USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 40 AIRFOIL (usa40-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.14 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa40-il-1000000.txt Download as CSV file: xf-usa40-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 40 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7142 0.04752 0.04516 -0.0792 1.0000 0.0259
-12.000 -0.7690 0.03979 0.03726 -0.0837 1.0000 0.0258
-11.750 -0.7827 0.03435 0.03154 -0.0900 0.9981 0.0258
-11.500 -0.7591 0.03031 0.02717 -0.0966 0.9950 0.0260
-11.250 -0.7316 0.02766 0.02426 -0.1007 0.9928 0.0262
-11.000 -0.7040 0.02579 0.02218 -0.1032 0.9894 0.0264
-10.750 -0.6734 0.02434 0.02056 -0.1057 0.9869 0.0266
-10.500 -0.6409 0.02326 0.01932 -0.1079 0.9851 0.0267
-10.250 -0.6123 0.02016 0.01594 -0.1110 0.9834 0.0271
-10.000 -0.5806 0.01883 0.01452 -0.1129 0.9814 0.0274
-9.750 -0.5517 0.01794 0.01359 -0.1138 0.9767 0.0277
-9.500 -0.5198 0.01723 0.01284 -0.1151 0.9734 0.0280
-9.250 -0.4874 0.01659 0.01214 -0.1164 0.9705 0.0284
-9.000 -0.4597 0.01597 0.01146 -0.1166 0.9637 0.0287
-8.750 -0.4299 0.01528 0.01070 -0.1173 0.9576 0.0290
-8.500 -0.4024 0.01466 0.01000 -0.1173 0.9482 0.0293
-8.250 -0.3742 0.01406 0.00932 -0.1175 0.9376 0.0295
-8.000 -0.3469 0.01354 0.00870 -0.1174 0.9251 0.0298
-7.750 -0.3200 0.01306 0.00814 -0.1172 0.9123 0.0301
-7.500 -0.2926 0.01264 0.00763 -0.1170 0.9008 0.0304
-7.250 -0.2651 0.01229 0.00718 -0.1169 0.8891 0.0306
-7.000 -0.2376 0.01199 0.00680 -0.1167 0.8767 0.0308
-6.750 -0.2110 0.01122 0.00595 -0.1166 0.8648 0.0314
-6.500 -0.1837 0.01078 0.00544 -0.1165 0.8525 0.0319
-6.250 -0.1560 0.01048 0.00508 -0.1164 0.8393 0.0324
-6.000 -0.1281 0.01024 0.00480 -0.1163 0.8262 0.0330
-5.750 -0.1002 0.01003 0.00452 -0.1162 0.8128 0.0337
-5.500 -0.0723 0.00982 0.00423 -0.1160 0.7982 0.0342
-5.250 -0.0444 0.00963 0.00395 -0.1159 0.7829 0.0348
-5.000 -0.0163 0.00947 0.00371 -0.1157 0.7674 0.0353
-4.750 0.0116 0.00922 0.00339 -0.1156 0.7507 0.0360
-4.500 0.0395 0.00900 0.00309 -0.1155 0.7332 0.0371
-4.250 0.0676 0.00888 0.00290 -0.1154 0.7160 0.0382
-4.000 0.0957 0.00878 0.00273 -0.1153 0.6996 0.0394
-3.750 0.1239 0.00871 0.00258 -0.1152 0.6833 0.0405
-3.500 0.1521 0.00857 0.00238 -0.1151 0.6679 0.0430
-3.250 0.1804 0.00850 0.00227 -0.1150 0.6543 0.0458
-2.750 0.2373 0.00831 0.00205 -0.1149 0.6284 0.0599
-2.500 0.2658 0.00824 0.00197 -0.1149 0.6161 0.0708
-2.250 0.2941 0.00820 0.00191 -0.1148 0.6037 0.0796
-2.000 0.3228 0.00812 0.00183 -0.1149 0.5917 0.0900
-1.750 0.3513 0.00802 0.00176 -0.1149 0.5787 0.1090
-1.500 0.3795 0.00785 0.00173 -0.1150 0.5627 0.1648
-1.250 0.4077 0.00783 0.00172 -0.1149 0.5450 0.1952
-1.000 0.4358 0.00785 0.00171 -0.1149 0.5250 0.2140
-0.750 0.4637 0.00789 0.00171 -0.1148 0.5044 0.2325
-0.500 0.4915 0.00792 0.00172 -0.1147 0.4830 0.2600
-0.250 0.5192 0.00786 0.00176 -0.1147 0.4628 0.3239
0.000 0.5471 0.00779 0.00182 -0.1148 0.4457 0.4006
0.250 0.5752 0.00772 0.00187 -0.1148 0.4316 0.4707
0.500 0.6032 0.00765 0.00196 -0.1148 0.4191 0.5479
0.750 0.6311 0.00767 0.00206 -0.1147 0.4071 0.6029
1.000 0.6587 0.00776 0.00216 -0.1146 0.3940 0.6425
1.250 0.6867 0.00783 0.00225 -0.1144 0.3834 0.6724
1.500 0.7145 0.00795 0.00236 -0.1143 0.3721 0.6951
1.750 0.7421 0.00809 0.00246 -0.1141 0.3601 0.7118
2.000 0.7701 0.00819 0.00255 -0.1139 0.3513 0.7293
2.250 0.7976 0.00834 0.00266 -0.1137 0.3413 0.7421
2.750 0.8530 0.00859 0.00287 -0.1134 0.3236 0.7644
3.000 0.8807 0.00871 0.00297 -0.1133 0.3150 0.7753
3.250 0.9079 0.00888 0.00309 -0.1131 0.3048 0.7859
3.500 0.9346 0.00907 0.00323 -0.1128 0.2903 0.7949
4.000 0.9882 0.00943 0.00350 -0.1123 0.2647 0.8147
4.250 1.0146 0.00965 0.00366 -0.1119 0.2505 0.8245
4.500 1.0402 0.00991 0.00385 -0.1115 0.2330 0.8367
4.750 1.0646 0.01023 0.00409 -0.1109 0.2113 0.8536
5.000 1.0865 0.01062 0.00440 -0.1098 0.1817 0.8847
5.250 1.1013 0.01174 0.00517 -0.1078 0.1022 1.0000
5.500 1.1241 0.01237 0.00565 -0.1071 0.0804 1.0000
5.750 1.1496 0.01271 0.00593 -0.1067 0.0728 1.0000
6.000 1.1745 0.01308 0.00624 -0.1062 0.0639 1.0000
6.250 1.1956 0.01382 0.00681 -0.1052 0.0345 1.0000
6.500 1.2206 0.01414 0.00713 -0.1048 0.0325 1.0000
6.750 1.2453 0.01448 0.00747 -0.1043 0.0316 1.0000
7.000 1.2696 0.01484 0.00785 -0.1037 0.0308 1.0000
7.250 1.2931 0.01524 0.00826 -0.1030 0.0299 1.0000
7.500 1.3159 0.01569 0.00873 -0.1022 0.0290 1.0000
7.750 1.3387 0.01611 0.00917 -0.1014 0.0286 1.0000
8.000 1.3614 0.01651 0.00959 -0.1007 0.0283 1.0000
8.250 1.3833 0.01696 0.01005 -0.0998 0.0279 1.0000
8.500 1.4045 0.01743 0.01055 -0.0988 0.0275 1.0000
8.750 1.4247 0.01794 0.01109 -0.0977 0.0271 1.0000
9.000 1.4439 0.01849 0.01167 -0.0964 0.0266 1.0000
9.250 1.4606 0.01910 0.01232 -0.0947 0.0261 1.0000
9.500 1.4744 0.01981 0.01306 -0.0926 0.0257 1.0000
9.750 1.4854 0.02067 0.01398 -0.0902 0.0253 1.0000
10.000 1.4916 0.02183 0.01522 -0.0873 0.0249 1.0000
10.250 1.5057 0.02253 0.01596 -0.0856 0.0248 1.0000
10.500 1.5187 0.02333 0.01681 -0.0838 0.0246 1.0000
10.750 1.5303 0.02426 0.01778 -0.0820 0.0244 1.0000
11.000 1.5410 0.02528 0.01886 -0.0802 0.0241 1.0000
11.250 1.5508 0.02643 0.02006 -0.0786 0.0238 1.0000
11.500 1.5591 0.02774 0.02143 -0.0769 0.0234 1.0000
11.750 1.5662 0.02923 0.02299 -0.0754 0.0232 1.0000
12.000 1.5717 0.03093 0.02474 -0.0740 0.0229 1.0000
12.250 1.5760 0.03284 0.02673 -0.0727 0.0227 1.0000
12.500 1.5786 0.03502 0.02898 -0.0716 0.0224 1.0000
12.750 1.5792 0.03751 0.03155 -0.0707 0.0222 1.0000
13.000 1.5776 0.04038 0.03450 -0.0700 0.0221 1.0000
13.250 1.5726 0.04376 0.03796 -0.0696 0.0219 1.0000
13.500 1.5641 0.04769 0.04199 -0.0694 0.0217 1.0000
13.750 1.5513 0.05228 0.04668 -0.0695 0.0215 1.0000
14.000 1.5330 0.05763 0.05214 -0.0697 0.0214 1.0000
14.250 1.5316 0.06108 0.05568 -0.0701 0.0212 1.0000
14.500 1.5320 0.06436 0.05904 -0.0705 0.0211 1.0000
14.750 1.5296 0.06805 0.06281 -0.0710 0.0209 1.0000
15.000 1.5253 0.07204 0.06689 -0.0716 0.0208 1.0000
15.250 1.5199 0.07624 0.07118 -0.0723 0.0207 1.0000
15.500 1.5142 0.08050 0.07552 -0.0731 0.0205 1.0000
15.750 1.5081 0.08484 0.07994 -0.0740 0.0204 1.0000
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