NACA 66(3)-418 (naca663418-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(3)-418 (naca663418-il) Reynolds number: 500,000 Max Cl/Cd: 89.88 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca663418-il-500000-n5.txt Download as CSV file: xf-naca663418-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-418
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6241 0.08951 0.08630 -0.1079 0.9430 0.0161
-17.500 -0.6700 0.07553 0.07197 -0.1181 0.9367 0.0162
-17.250 -0.6898 0.06736 0.06353 -0.1245 0.9278 0.0162
-17.000 -0.7040 0.06133 0.05724 -0.1285 0.9172 0.0162
-16.750 -0.7140 0.05685 0.05254 -0.1306 0.9069 0.0163
-16.500 -0.7235 0.05292 0.04839 -0.1319 0.8977 0.0164
-16.250 -0.7318 0.04954 0.04480 -0.1323 0.8892 0.0166
-15.750 -0.7394 0.04425 0.03914 -0.1320 0.8747 0.0167
-15.500 -0.7399 0.04215 0.03685 -0.1315 0.8681 0.0170
-15.250 -0.7387 0.04026 0.03478 -0.1308 0.8622 0.0172
-15.000 -0.7368 0.03837 0.03272 -0.1300 0.8566 0.0173
-14.750 -0.7331 0.03677 0.03095 -0.1290 0.8510 0.0175
-14.500 -0.7276 0.03528 0.02929 -0.1281 0.8464 0.0176
-14.250 -0.7209 0.03384 0.02774 -0.1271 0.8421 0.0178
-14.000 -0.7118 0.03260 0.02639 -0.1262 0.8377 0.0178
-13.750 -0.7024 0.03144 0.02516 -0.1252 0.8335 0.0181
-13.500 -0.6917 0.03040 0.02403 -0.1243 0.8297 0.0183
-13.250 -0.6800 0.02944 0.02298 -0.1234 0.8263 0.0184
-13.000 -0.6673 0.02855 0.02203 -0.1225 0.8227 0.0185
-12.750 -0.6544 0.02768 0.02109 -0.1216 0.8191 0.0188
-12.500 -0.6406 0.02690 0.02023 -0.1207 0.8157 0.0190
-12.250 -0.6265 0.02610 0.01933 -0.1197 0.8126 0.0192
-12.000 -0.6114 0.02534 0.01850 -0.1188 0.8098 0.0194
-11.750 -0.5961 0.02461 0.01771 -0.1179 0.8068 0.0198
-11.500 -0.5802 0.02395 0.01697 -0.1170 0.8038 0.0201
-11.250 -0.5641 0.02329 0.01622 -0.1161 0.8009 0.0205
-11.000 -0.5474 0.02269 0.01554 -0.1152 0.7982 0.0207
-10.750 -0.5306 0.02212 0.01488 -0.1143 0.7957 0.0211
-10.500 -0.5153 0.02141 0.01413 -0.1132 0.7933 0.0213
-10.250 -0.4995 0.02077 0.01347 -0.1122 0.7907 0.0216
-10.000 -0.4834 0.02018 0.01285 -0.1111 0.7880 0.0219
-9.750 -0.4664 0.01966 0.01231 -0.1101 0.7853 0.0222
-9.500 -0.4493 0.01917 0.01179 -0.1091 0.7829 0.0227
-9.250 -0.4321 0.01869 0.01126 -0.1081 0.7807 0.0232
-9.000 -0.4153 0.01820 0.01071 -0.1070 0.7787 0.0235
-8.750 -0.3977 0.01776 0.01022 -0.1060 0.7768 0.0241
-8.500 -0.3801 0.01731 0.00975 -0.1049 0.7748 0.0246
-8.250 -0.3620 0.01691 0.00931 -0.1039 0.7728 0.0250
-8.000 -0.3461 0.01640 0.00880 -0.1025 0.7707 0.0257
-7.750 -0.3285 0.01599 0.00839 -0.1014 0.7687 0.0265
-7.500 -0.3100 0.01564 0.00802 -0.1004 0.7668 0.0275
-7.250 -0.2918 0.01529 0.00763 -0.0993 0.7651 0.0283
-7.000 -0.2731 0.01496 0.00726 -0.0982 0.7634 0.0293
-6.750 -0.2552 0.01460 0.00688 -0.0970 0.7618 0.0302
-6.500 -0.2375 0.01426 0.00652 -0.0957 0.7603 0.0317
-6.250 -0.2192 0.01395 0.00621 -0.0945 0.7588 0.0330
-6.000 -0.2008 0.01368 0.00592 -0.0933 0.7572 0.0346
-5.750 -0.1841 0.01337 0.00563 -0.0917 0.7555 0.0370
-5.500 -0.1674 0.01314 0.00541 -0.0901 0.7539 0.0399
-5.250 -0.1524 0.01292 0.00520 -0.0882 0.7522 0.0435
-5.000 -0.1361 0.01270 0.00500 -0.0864 0.7505 0.0497
-4.750 -0.1178 0.01245 0.00479 -0.0851 0.7489 0.0608
-4.500 -0.1006 0.01213 0.00456 -0.0836 0.7475 0.0848
-4.250 -0.0857 0.01169 0.00431 -0.0817 0.7462 0.1320
-4.000 -0.0725 0.01114 0.00404 -0.0797 0.7449 0.2047
-3.750 -0.0589 0.01055 0.00377 -0.0777 0.7436 0.2858
-3.500 -0.0464 0.00985 0.00347 -0.0757 0.7423 0.3850
-3.250 -0.0341 0.00899 0.00311 -0.0736 0.7409 0.5054
-3.000 -0.0166 0.00852 0.00318 -0.0720 0.7397 0.6415
-2.750 0.0107 0.00860 0.00330 -0.0720 0.7385 0.6737
-2.500 0.0385 0.00874 0.00346 -0.0721 0.7374 0.6923
-2.250 0.0666 0.00888 0.00356 -0.0723 0.7364 0.7053
-2.000 0.0949 0.00905 0.00378 -0.0724 0.7353 0.7138
-1.750 0.1234 0.00912 0.00382 -0.0727 0.7343 0.7190
-1.500 0.1521 0.00916 0.00380 -0.0732 0.7333 0.7227
-1.250 0.1808 0.00920 0.00384 -0.0735 0.7323 0.7253
-1.000 0.2096 0.00923 0.00387 -0.0740 0.7313 0.7273
-0.750 0.2386 0.00924 0.00386 -0.0745 0.7303 0.7286
-0.500 0.2678 0.00926 0.00385 -0.0750 0.7294 0.7295
-0.250 0.2972 0.00928 0.00385 -0.0757 0.7286 0.7305
0.000 0.3266 0.00932 0.00387 -0.0763 0.7277 0.7318
0.250 0.3547 0.00935 0.00390 -0.0767 0.7269 0.7329
0.500 0.3826 0.00937 0.00395 -0.0770 0.7259 0.7339
0.750 0.4105 0.00940 0.00399 -0.0774 0.7248 0.7350
1.000 0.4383 0.00943 0.00404 -0.0777 0.7235 0.7360
1.250 0.4661 0.00946 0.00407 -0.0780 0.7218 0.7370
1.500 0.4941 0.00946 0.00408 -0.0783 0.7196 0.7380
1.750 0.5225 0.00945 0.00408 -0.0787 0.7172 0.7390
2.000 0.5515 0.00944 0.00406 -0.0792 0.7149 0.7399
2.250 0.5807 0.00943 0.00405 -0.0798 0.7129 0.7408
2.500 0.6098 0.00946 0.00410 -0.0803 0.7110 0.7418
2.750 0.6348 0.00949 0.00421 -0.0800 0.7084 0.7430
3.000 0.6605 0.00950 0.00427 -0.0798 0.7048 0.7441
3.250 0.6873 0.00948 0.00428 -0.0799 0.7008 0.7451
3.500 0.7156 0.00944 0.00426 -0.0802 0.6972 0.7462
3.750 0.7410 0.00944 0.00430 -0.0799 0.6922 0.7473
4.000 0.7639 0.00941 0.00433 -0.0791 0.6850 0.7486
4.250 0.7898 0.00937 0.00428 -0.0788 0.6778 0.7498
4.500 0.8108 0.00938 0.00436 -0.0777 0.6690 0.7512
4.750 0.8306 0.00937 0.00436 -0.0762 0.6554 0.7526
5.000 0.8431 0.00938 0.00433 -0.0732 0.6270 0.7542
5.250 0.8303 0.00968 0.00434 -0.0651 0.5677 0.7563
5.500 0.8098 0.01065 0.00500 -0.0562 0.5125 0.7584
5.750 0.7962 0.01171 0.00584 -0.0491 0.4645 0.7604
6.000 0.7869 0.01284 0.00677 -0.0432 0.4199 0.7625
6.250 0.7811 0.01400 0.00774 -0.0382 0.3755 0.7646
6.500 0.7795 0.01513 0.00869 -0.0341 0.3344 0.7667
6.750 0.7794 0.01629 0.00964 -0.0304 0.2912 0.7691
7.000 0.7797 0.01750 0.01062 -0.0269 0.2435 0.7715
7.250 0.7839 0.01860 0.01151 -0.0241 0.2022 0.7736
7.500 0.7854 0.01990 0.01251 -0.0211 0.1493 0.7755
7.750 0.7911 0.02100 0.01342 -0.0187 0.1079 0.7774
8.000 0.8000 0.02198 0.01426 -0.0167 0.0793 0.7794
8.500 0.8246 0.02368 0.01580 -0.0137 0.0446 0.7835
8.750 0.8390 0.02444 0.01654 -0.0125 0.0372 0.7857
9.000 0.8548 0.02514 0.01724 -0.0116 0.0331 0.7880
9.250 0.8705 0.02587 0.01797 -0.0106 0.0298 0.7903
9.500 0.8866 0.02658 0.01869 -0.0097 0.0273 0.7926
9.750 0.9018 0.02734 0.01948 -0.0088 0.0255 0.7947
10.000 0.9176 0.02807 0.02026 -0.0079 0.0238 0.7970
10.250 0.9325 0.02887 0.02109 -0.0070 0.0225 0.7995
10.500 0.9474 0.02969 0.02195 -0.0060 0.0212 0.8022
10.750 0.9625 0.03051 0.02282 -0.0052 0.0199 0.8050
11.000 0.9769 0.03140 0.02374 -0.0044 0.0188 0.8078
11.250 0.9909 0.03235 0.02471 -0.0035 0.0178 0.8106
11.500 1.0053 0.03325 0.02568 -0.0027 0.0171 0.8132
11.750 1.0187 0.03422 0.02672 -0.0018 0.0163 0.8163
12.000 1.0322 0.03522 0.02776 -0.0010 0.0158 0.8196
12.250 1.0448 0.03630 0.02889 -0.0001 0.0155 0.8231
12.500 1.0558 0.03754 0.03017 0.0008 0.0148 0.8268
12.750 1.0681 0.03870 0.03141 0.0016 0.0145 0.8302
13.000 1.0798 0.03988 0.03268 0.0024 0.0141 0.8339
13.250 1.0904 0.04119 0.03406 0.0032 0.0138 0.8378
13.500 1.1014 0.04251 0.03545 0.0039 0.0136 0.8418
13.750 1.1121 0.04388 0.03689 0.0046 0.0133 0.8458
14.000 1.1213 0.04536 0.03845 0.0054 0.0131 0.8498
14.250 1.1306 0.04687 0.04004 0.0061 0.0130 0.8544
14.500 1.1390 0.04851 0.04175 0.0067 0.0127 0.8592
14.750 1.1461 0.05029 0.04360 0.0074 0.0125 0.8638
15.000 1.1523 0.05215 0.04555 0.0081 0.0123 0.8691
15.250 1.1572 0.05419 0.04768 0.0087 0.0122 0.8747
15.500 1.1643 0.05608 0.04967 0.0092 0.0121 0.8806
15.750 1.1701 0.05806 0.05178 0.0097 0.0120 0.8875
16.000 1.1756 0.06014 0.05396 0.0101 0.0119 0.8950
16.250 1.1801 0.06228 0.05622 0.0105 0.0117 0.9036
16.500 1.1841 0.06459 0.05865 0.0108 0.0117 0.9131
16.750 1.1880 0.06695 0.06113 0.0110 0.0116 0.9247
17.000 1.1924 0.06955 0.06386 0.0107 0.0114 0.9390
17.250 1.1998 0.07238 0.06683 0.0094 0.0113 0.9577
17.500 1.2021 0.07511 0.06967 0.0090 0.0113 1.0000
17.750 1.2041 0.07814 0.07279 0.0084 0.0111 1.0000
18.000 1.2061 0.08123 0.07598 0.0077 0.0110 1.0000
18.250 1.2078 0.08443 0.07927 0.0068 0.0110 1.0000
18.500 1.2085 0.08782 0.08277 0.0059 0.0109 1.0000
18.750 1.2084 0.09137 0.08642 0.0047 0.0108 1.0000
19.000 1.2081 0.09500 0.09016 0.0034 0.0107 1.0000
19.250 1.2066 0.09886 0.09412 0.0020 0.0106 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(3)-418 (naca663418-il)