USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27m2-il-1000000-n5.txt Download as CSV file: xf-usa27m2-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 mod. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4085 0.03368 0.03102 -0.1222 0.9418 0.0185
-10.000 -0.4165 0.02880 0.02563 -0.1209 0.9313 0.0186
-9.750 -0.4135 0.02592 0.02243 -0.1190 0.9222 0.0188
-9.500 -0.3977 0.02434 0.02067 -0.1181 0.9154 0.0189
-9.250 -0.3803 0.02323 0.01943 -0.1169 0.9075 0.0190
-9.000 -0.3605 0.02223 0.01828 -0.1161 0.9004 0.0191
-8.750 -0.3403 0.02143 0.01736 -0.1152 0.8921 0.0192
-8.500 -0.3187 0.02074 0.01654 -0.1144 0.8825 0.0193
-8.250 -0.2975 0.02009 0.01577 -0.1134 0.8697 0.0195
-8.000 -0.2764 0.01943 0.01497 -0.1124 0.8565 0.0196
-7.750 -0.2555 0.01867 0.01405 -0.1114 0.8456 0.0197
-7.500 -0.2343 0.01794 0.01316 -0.1103 0.8353 0.0199
-7.250 -0.2124 0.01722 0.01231 -0.1093 0.8257 0.0200
-7.000 -0.1905 0.01654 0.01148 -0.1083 0.8161 0.0202
-6.750 -0.1682 0.01589 0.01069 -0.1073 0.8047 0.0204
-6.500 -0.1458 0.01529 0.00994 -0.1063 0.7921 0.0205
-6.250 -0.1233 0.01473 0.00924 -0.1052 0.7780 0.0207
-6.000 -0.1010 0.01423 0.00859 -0.1041 0.7610 0.0208
-5.750 -0.0794 0.01379 0.00799 -0.1028 0.7374 0.0210
-5.500 -0.0599 0.01349 0.00747 -0.1010 0.6990 0.0211
-5.250 -0.0406 0.01324 0.00702 -0.0991 0.6634 0.0212
-5.000 -0.0188 0.01296 0.00658 -0.0979 0.6427 0.0213
-4.750 0.0043 0.01265 0.00617 -0.0969 0.6290 0.0215
-4.500 0.0279 0.01237 0.00579 -0.0959 0.6179 0.0216
-4.250 0.0523 0.01212 0.00548 -0.0952 0.6081 0.0218
-4.000 0.0767 0.01194 0.00522 -0.0944 0.5987 0.0220
-3.750 0.1013 0.01176 0.00497 -0.0936 0.5886 0.0221
-3.500 0.1258 0.01155 0.00471 -0.0929 0.5792 0.0222
-3.250 0.1492 0.01118 0.00429 -0.0920 0.5693 0.0224
-3.000 0.1732 0.01089 0.00396 -0.0911 0.5599 0.0226
-2.750 0.1970 0.01071 0.00373 -0.0903 0.5486 0.0228
-2.500 0.2212 0.01057 0.00355 -0.0894 0.5349 0.0231
-2.250 0.2450 0.01047 0.00339 -0.0885 0.5184 0.0233
-2.000 0.2680 0.01043 0.00326 -0.0875 0.4971 0.0235
-1.750 0.2905 0.01043 0.00314 -0.0864 0.4722 0.0238
-1.500 0.3129 0.01045 0.00305 -0.0852 0.4504 0.0241
-1.250 0.3362 0.01045 0.00297 -0.0842 0.4333 0.0243
-1.000 0.3598 0.01044 0.00289 -0.0833 0.4187 0.0246
-0.750 0.3836 0.01044 0.00282 -0.0825 0.4049 0.0249
-0.500 0.4075 0.01044 0.00277 -0.0816 0.3923 0.0252
-0.250 0.4315 0.01045 0.00272 -0.0808 0.3820 0.0255
0.000 0.4566 0.01042 0.00267 -0.0802 0.3755 0.0258
0.250 0.4813 0.01043 0.00264 -0.0795 0.3689 0.0261
0.500 0.5059 0.01039 0.00259 -0.0788 0.3637 0.0267
0.750 0.5307 0.01036 0.00254 -0.0782 0.3586 0.0274
1.000 0.5554 0.01037 0.00253 -0.0775 0.3532 0.0280
1.250 0.5799 0.01039 0.00253 -0.0768 0.3478 0.0287
1.500 0.6049 0.01041 0.00254 -0.0763 0.3427 0.0294
1.750 0.6295 0.01046 0.00256 -0.0756 0.3369 0.0302
2.000 0.6538 0.01052 0.00259 -0.0749 0.3316 0.0310
2.250 0.6790 0.01054 0.00262 -0.0744 0.3285 0.0330
2.750 0.7251 0.01032 0.00274 -0.0726 0.3198 0.1912
3.000 0.7482 0.01031 0.00284 -0.0717 0.3159 0.2415
3.250 0.7721 0.01033 0.00293 -0.0710 0.3133 0.2698
3.750 0.8200 0.01038 0.00312 -0.0696 0.3074 0.3244
4.000 0.8435 0.01042 0.00323 -0.0688 0.3041 0.3574
4.250 0.8662 0.01039 0.00334 -0.0679 0.3007 0.4262
4.500 0.8914 0.00944 0.00378 -0.0675 0.2975 0.9643
4.750 0.9297 0.00966 0.00399 -0.0700 0.2933 0.9807
5.000 0.9663 0.00988 0.00418 -0.0721 0.2882 0.9854
5.250 1.0010 0.01010 0.00437 -0.0739 0.2839 0.9886
5.500 1.0327 0.01028 0.00453 -0.0750 0.2806 0.9917
5.750 1.0638 0.01047 0.00470 -0.0760 0.2738 0.9939
6.000 1.0979 0.01074 0.00490 -0.0778 0.2643 0.9957
6.250 1.1290 0.01101 0.00511 -0.0789 0.2530 0.9974
6.500 1.1588 0.01131 0.00534 -0.0798 0.2393 0.9990
6.750 1.1802 0.01176 0.00564 -0.0789 0.2147 1.0000
7.000 1.1838 0.01223 0.00597 -0.0743 0.1906 1.0000
7.250 1.1920 0.01262 0.00628 -0.0706 0.1764 1.0000
7.500 1.2033 0.01295 0.00656 -0.0675 0.1683 1.0000
7.750 1.2176 0.01321 0.00681 -0.0651 0.1634 1.0000
8.000 1.2322 0.01350 0.00709 -0.0628 0.1585 1.0000
8.250 1.2457 0.01387 0.00742 -0.0603 0.1521 1.0000
8.500 1.2619 0.01415 0.00771 -0.0584 0.1474 1.0000
8.750 1.2763 0.01455 0.00807 -0.0562 0.1404 1.0000
9.000 1.2917 0.01494 0.00844 -0.0542 0.1334 1.0000
9.250 1.3050 0.01548 0.00890 -0.0521 0.1216 1.0000
9.500 1.3049 0.01673 0.00990 -0.0479 0.0843 1.0000
9.750 1.2955 0.01855 0.01147 -0.0426 0.0398 1.0000
10.000 1.2982 0.01981 0.01267 -0.0393 0.0174 1.0000
10.250 1.3117 0.02049 0.01337 -0.0376 0.0154 1.0000
10.500 1.3256 0.02117 0.01408 -0.0360 0.0142 1.0000
10.750 1.3397 0.02186 0.01481 -0.0346 0.0136 1.0000
11.000 1.3530 0.02261 0.01559 -0.0331 0.0129 1.0000
11.250 1.3653 0.02346 0.01647 -0.0315 0.0123 1.0000
11.500 1.3765 0.02440 0.01745 -0.0300 0.0117 1.0000
11.750 1.3875 0.02539 0.01848 -0.0285 0.0112 1.0000
12.000 1.3989 0.02636 0.01949 -0.0271 0.0108 1.0000
12.250 1.4097 0.02741 0.02059 -0.0258 0.0105 1.0000
12.500 1.4198 0.02855 0.02178 -0.0245 0.0102 1.0000
12.750 1.4287 0.02981 0.02309 -0.0232 0.0099 1.0000
13.000 1.4367 0.03118 0.02451 -0.0219 0.0095 1.0000
13.250 1.4437 0.03269 0.02607 -0.0207 0.0093 1.0000
13.500 1.4493 0.03439 0.02783 -0.0195 0.0090 1.0000
13.750 1.4528 0.03635 0.02986 -0.0184 0.0087 1.0000
14.000 1.4577 0.03825 0.03183 -0.0176 0.0086 1.0000
14.250 1.4625 0.04025 0.03390 -0.0168 0.0084 1.0000
14.500 1.4665 0.04242 0.03614 -0.0163 0.0083 1.0000
14.750 1.4695 0.04477 0.03856 -0.0159 0.0081 1.0000
15.000 1.4713 0.04731 0.04117 -0.0155 0.0079 1.0000
15.250 1.4719 0.05004 0.04398 -0.0153 0.0077 1.0000
15.500 1.4716 0.05294 0.04695 -0.0152 0.0076 1.0000
15.750 1.4700 0.05603 0.05013 -0.0152 0.0074 1.0000
16.000 1.4669 0.05935 0.05353 -0.0153 0.0073 1.0000
16.250 1.4621 0.06293 0.05719 -0.0155 0.0072 1.0000
16.500 1.4559 0.06676 0.06112 -0.0158 0.0071 1.0000
16.750 1.4486 0.07085 0.06529 -0.0163 0.0070 1.0000
17.000 1.4402 0.07513 0.06967 -0.0170 0.0069 1.0000
17.250 1.4300 0.07971 0.07435 -0.0177 0.0068 1.0000
17.500 1.4189 0.08452 0.07927 -0.0187 0.0067 1.0000
17.750 1.4069 0.08951 0.08436 -0.0198 0.0067 1.0000
18.000 1.3938 0.09468 0.08963 -0.0210 0.0066 1.0000
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