NACA 63(3)-618 (naca633618-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(3)-618 (naca633618-il) Reynolds number: 500,000 Max Cl/Cd: 107.65 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633618-il-500000.txt Download as CSV file: xf-naca633618-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-618
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -0.8251 0.09367 0.09003 -0.0706 1.0000 0.0217
-18.250 -0.8330 0.08870 0.08498 -0.0735 1.0000 0.0219
-18.000 -0.8430 0.08350 0.07968 -0.0764 1.0000 0.0220
-17.750 -0.8478 0.07919 0.07530 -0.0788 1.0000 0.0224
-17.500 -0.8561 0.07456 0.07055 -0.0813 1.0000 0.0226
-17.250 -0.8619 0.07036 0.06626 -0.0835 1.0000 0.0229
-17.000 -0.8682 0.06626 0.06204 -0.0855 1.0000 0.0231
-16.750 -0.8725 0.06255 0.05821 -0.0873 1.0000 0.0234
-16.500 -0.8763 0.05903 0.05457 -0.0888 1.0000 0.0237
-16.250 -0.8790 0.05575 0.05115 -0.0902 1.0000 0.0241
-16.000 -0.8816 0.05256 0.04782 -0.0916 1.0000 0.0244
-15.750 -0.8815 0.04999 0.04517 -0.0919 1.0000 0.0248
-15.500 -0.8783 0.04783 0.04301 -0.0922 1.0000 0.0252
-15.250 -0.8739 0.04583 0.04098 -0.0926 1.0000 0.0256
-15.000 -0.8700 0.04387 0.03899 -0.0928 1.0000 0.0260
-14.750 -0.8661 0.04199 0.03706 -0.0930 1.0000 0.0265
-14.500 -0.8625 0.04017 0.03517 -0.0928 1.0000 0.0271
-14.250 -0.8593 0.03838 0.03329 -0.0926 1.0000 0.0277
-14.000 -0.8561 0.03674 0.03155 -0.0922 1.0000 0.0283
-13.750 -0.8539 0.03516 0.02993 -0.0911 1.0000 0.0289
-13.500 -0.8520 0.03385 0.02865 -0.0897 1.0000 0.0294
-13.250 -0.8445 0.03262 0.02742 -0.0894 0.9990 0.0301
-13.000 -0.8169 0.03102 0.02577 -0.0928 0.9893 0.0312
-12.750 -0.7901 0.02948 0.02411 -0.0959 0.9795 0.0324
-12.500 -0.7624 0.02791 0.02248 -0.0989 0.9702 0.0336
-12.250 -0.7290 0.02656 0.02113 -0.1028 0.9616 0.0349
-12.000 -0.6909 0.02530 0.01979 -0.1075 0.9532 0.0365
-11.750 -0.6532 0.02409 0.01844 -0.1119 0.9410 0.0382
-11.500 -0.6216 0.02288 0.01722 -0.1150 0.9259 0.0398
-11.250 -0.5977 0.02206 0.01629 -0.1163 0.9091 0.0413
-11.000 -0.5806 0.02135 0.01546 -0.1160 0.8935 0.0425
-10.750 -0.5648 0.02075 0.01471 -0.1152 0.8803 0.0434
-10.500 -0.5572 0.01973 0.01366 -0.1135 0.8677 0.0449
-10.250 -0.5464 0.01902 0.01292 -0.1120 0.8564 0.0461
-10.000 -0.5345 0.01844 0.01224 -0.1105 0.8465 0.0474
-9.750 -0.5245 0.01794 0.01167 -0.1086 0.8366 0.0486
-9.500 -0.5077 0.01752 0.01111 -0.1076 0.8287 0.0497
-9.250 -0.4968 0.01664 0.01024 -0.1062 0.8200 0.0514
-9.000 -0.4779 0.01618 0.00972 -0.1054 0.8127 0.0532
-8.750 -0.4573 0.01576 0.00925 -0.1048 0.8055 0.0551
-8.500 -0.4346 0.01544 0.00885 -0.1044 0.7986 0.0568
-8.250 -0.4157 0.01478 0.00816 -0.1038 0.7922 0.0595
-8.000 -0.3928 0.01438 0.00774 -0.1034 0.7854 0.0621
-7.750 -0.3684 0.01406 0.00734 -0.1032 0.7790 0.0647
-7.500 -0.3455 0.01353 0.00680 -0.1030 0.7731 0.0688
-7.250 -0.3202 0.01319 0.00644 -0.1029 0.7669 0.0735
-7.000 -0.2956 0.01271 0.00597 -0.1029 0.7608 0.0815
-6.750 -0.2700 0.01229 0.00555 -0.1030 0.7552 0.0945
-6.500 -0.2446 0.01175 0.00515 -0.1032 0.7491 0.1203
-6.250 -0.2187 0.01119 0.00474 -0.1036 0.7433 0.1582
-6.000 -0.1919 0.01066 0.00436 -0.1040 0.7380 0.2045
-5.750 -0.1649 0.01004 0.00400 -0.1047 0.7322 0.2654
-5.500 -0.1370 0.00950 0.00369 -0.1053 0.7264 0.3285
-5.250 -0.1082 0.00921 0.00352 -0.1059 0.7212 0.3821
-5.000 -0.0789 0.00906 0.00344 -0.1064 0.7159 0.4144
-4.750 -0.0496 0.00898 0.00337 -0.1067 0.7102 0.4362
-4.500 -0.0202 0.00894 0.00330 -0.1071 0.7049 0.4528
-4.250 0.0093 0.00893 0.00326 -0.1074 0.6998 0.4669
-4.000 0.0388 0.00891 0.00322 -0.1078 0.6944 0.4789
-3.750 0.0684 0.00893 0.00318 -0.1081 0.6892 0.4918
-3.500 0.0979 0.00898 0.00321 -0.1084 0.6842 0.5055
-3.250 0.1272 0.00897 0.00322 -0.1087 0.6789 0.5160
-3.000 0.1567 0.00901 0.00321 -0.1090 0.6735 0.5252
-2.750 0.1861 0.00903 0.00318 -0.1092 0.6688 0.5323
-2.500 0.2155 0.00907 0.00320 -0.1095 0.6641 0.5397
-2.250 0.2450 0.00910 0.00321 -0.1099 0.6589 0.5482
-2.000 0.2741 0.00912 0.00323 -0.1101 0.6539 0.5551
-1.750 0.3036 0.00920 0.00322 -0.1104 0.6491 0.5610
-1.500 0.3330 0.00919 0.00321 -0.1107 0.6443 0.5663
-1.250 0.3620 0.00918 0.00323 -0.1110 0.6395 0.5714
-1.000 0.3914 0.00923 0.00324 -0.1113 0.6350 0.5769
-0.750 0.4210 0.00932 0.00325 -0.1117 0.6305 0.5824
-0.500 0.4499 0.00929 0.00328 -0.1119 0.6257 0.5875
-0.250 0.4789 0.00932 0.00331 -0.1121 0.6208 0.5925
0.000 0.5082 0.00939 0.00333 -0.1124 0.6164 0.5979
0.250 0.5376 0.00946 0.00337 -0.1128 0.6121 0.6029
0.500 0.5663 0.00946 0.00342 -0.1130 0.6075 0.6075
0.750 0.5953 0.00950 0.00347 -0.1133 0.6029 0.6125
1.000 0.6245 0.00960 0.00351 -0.1136 0.5984 0.6180
1.250 0.6535 0.00965 0.00358 -0.1139 0.5942 0.6229
1.500 0.6821 0.00968 0.00366 -0.1141 0.5896 0.6276
1.750 0.7109 0.00973 0.00372 -0.1143 0.5850 0.6328
2.000 0.7400 0.00986 0.00378 -0.1146 0.5806 0.6383
2.250 0.7684 0.00990 0.00389 -0.1148 0.5761 0.6435
2.500 0.7967 0.00995 0.00399 -0.1149 0.5713 0.6488
2.750 0.8253 0.01003 0.00406 -0.1151 0.5667 0.6545
3.000 0.8542 0.01018 0.00417 -0.1154 0.5622 0.6597
3.250 0.8819 0.01021 0.00430 -0.1155 0.5578 0.6649
3.500 0.9101 0.01028 0.00441 -0.1156 0.5530 0.6707
3.750 0.9385 0.01040 0.00451 -0.1159 0.5485 0.6767
4.000 0.9664 0.01052 0.00466 -0.1159 0.5439 0.6823
4.250 0.9938 0.01058 0.00481 -0.1160 0.5389 0.6882
4.500 1.0215 0.01067 0.00491 -0.1160 0.5335 0.6943
4.750 1.0489 0.01082 0.00504 -0.1160 0.5276 0.6998
5.000 1.0753 0.01086 0.00519 -0.1158 0.5213 0.7060
5.250 1.1022 0.01097 0.00531 -0.1158 0.5150 0.7128
5.500 1.1286 0.01110 0.00547 -0.1156 0.5090 0.7187
5.750 1.1546 0.01117 0.00563 -0.1154 0.5021 0.7250
6.000 1.1807 0.01134 0.00577 -0.1152 0.4953 0.7318
6.250 1.2060 0.01143 0.00597 -0.1148 0.4880 0.7380
6.500 1.2303 0.01158 0.00612 -0.1142 0.4790 0.7451
6.750 1.2545 0.01171 0.00630 -0.1137 0.4681 0.7520
7.000 1.2768 0.01188 0.00650 -0.1128 0.4564 0.7585
7.250 1.2992 0.01210 0.00672 -0.1120 0.4448 0.7662
7.500 1.3219 0.01228 0.00697 -0.1112 0.4339 0.7732
7.750 1.3428 0.01253 0.00724 -0.1101 0.4221 0.7808
8.000 1.3621 0.01283 0.00754 -0.1088 0.4087 0.7885
8.250 1.3791 0.01317 0.00789 -0.1071 0.3935 0.7965
8.500 1.3931 0.01355 0.00825 -0.1048 0.3759 0.8053
8.750 1.4023 0.01401 0.00871 -0.1017 0.3553 0.8142
9.000 1.4074 0.01471 0.00933 -0.0982 0.3315 0.8240
9.250 1.4100 0.01556 0.01011 -0.0945 0.3070 0.8350
9.500 1.4098 0.01658 0.01107 -0.0906 0.2825 0.8469
9.750 1.4095 0.01772 0.01215 -0.0870 0.2585 0.8605
10.000 1.4073 0.01901 0.01339 -0.0834 0.2357 0.8768
10.250 1.4039 0.02037 0.01473 -0.0797 0.2152 0.8988
10.500 1.3987 0.02165 0.01603 -0.0758 0.1971 0.9549
10.750 1.4001 0.02339 0.01768 -0.0739 0.1769 1.0000
11.000 1.4005 0.02535 0.01953 -0.0721 0.1583 1.0000
11.250 1.4014 0.02734 0.02144 -0.0705 0.1415 1.0000
11.500 1.4020 0.02943 0.02345 -0.0690 0.1250 1.0000
11.750 1.4022 0.03162 0.02558 -0.0676 0.1101 1.0000
12.000 1.4016 0.03396 0.02786 -0.0663 0.0962 1.0000
12.250 1.4006 0.03642 0.03025 -0.0651 0.0838 1.0000
12.500 1.3999 0.03896 0.03275 -0.0641 0.0731 1.0000
12.750 1.4007 0.04145 0.03522 -0.0633 0.0650 1.0000
13.000 1.4020 0.04399 0.03776 -0.0627 0.0589 1.0000
13.250 1.4021 0.04672 0.04048 -0.0621 0.0541 1.0000
13.500 1.4063 0.04911 0.04291 -0.0618 0.0506 1.0000
13.750 1.4062 0.05202 0.04583 -0.0615 0.0477 1.0000
14.000 1.4110 0.05447 0.04835 -0.0613 0.0456 1.0000
14.250 1.4145 0.05712 0.05104 -0.0613 0.0435 1.0000
14.500 1.4146 0.06024 0.05419 -0.0613 0.0418 1.0000
14.750 1.4170 0.06313 0.05715 -0.0614 0.0404 1.0000
15.000 1.4217 0.06578 0.05988 -0.0616 0.0390 1.0000
15.250 1.4241 0.06880 0.06294 -0.0619 0.0377 1.0000
15.500 1.4237 0.07221 0.06639 -0.0623 0.0365 1.0000
15.750 1.4235 0.07565 0.06990 -0.0628 0.0354 1.0000
16.000 1.4276 0.07858 0.07291 -0.0633 0.0344 1.0000
16.250 1.4311 0.08162 0.07602 -0.0638 0.0333 1.0000
16.500 1.4323 0.08504 0.07950 -0.0646 0.0322 1.0000
16.750 1.4298 0.08900 0.08350 -0.0655 0.0313 1.0000
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