USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 40 AIRFOIL (usa40-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.02 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa40-il-1000000-n5.txt Download as CSV file: xf-usa40-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8709 0.06217 0.05952 -0.0678 1.0000 0.0214
-14.500 -0.9282 0.04797 0.04506 -0.0797 1.0000 0.0214
-14.250 -0.9512 0.03931 0.03620 -0.0883 1.0000 0.0214
-14.000 -0.9653 0.03403 0.03076 -0.0932 1.0000 0.0215
-13.750 -0.9798 0.03065 0.02726 -0.0948 1.0000 0.0215
-13.500 -0.9702 0.02845 0.02492 -0.0968 0.9991 0.0216
-13.250 -0.9427 0.02672 0.02306 -0.1001 0.9964 0.0218
-13.000 -0.9135 0.02527 0.02149 -0.1030 0.9941 0.0220
-12.750 -0.8854 0.02397 0.02008 -0.1051 0.9910 0.0221
-12.500 -0.8571 0.02276 0.01876 -0.1070 0.9874 0.0222
-12.250 -0.8277 0.02167 0.01757 -0.1089 0.9848 0.0224
-12.000 -0.7976 0.02070 0.01649 -0.1106 0.9825 0.0225
-11.750 -0.7715 0.01985 0.01556 -0.1112 0.9772 0.0226
-11.500 -0.7422 0.01905 0.01467 -0.1124 0.9729 0.0227
-11.250 -0.7126 0.01832 0.01386 -0.1134 0.9688 0.0228
-11.000 -0.6850 0.01766 0.01312 -0.1140 0.9625 0.0228
-10.750 -0.6562 0.01669 0.01206 -0.1150 0.9567 0.0230
-10.500 -0.6292 0.01592 0.01122 -0.1155 0.9482 0.0233
-10.250 -0.6009 0.01529 0.01053 -0.1160 0.9399 0.0235
-10.000 -0.5734 0.01476 0.00994 -0.1162 0.9300 0.0236
-9.750 -0.5458 0.01429 0.00940 -0.1164 0.9211 0.0238
-9.500 -0.5185 0.01387 0.00891 -0.1165 0.9109 0.0240
-9.250 -0.4911 0.01348 0.00845 -0.1165 0.9009 0.0242
-9.000 -0.4638 0.01312 0.00801 -0.1164 0.8901 0.0244
-8.750 -0.4364 0.01278 0.00760 -0.1164 0.8781 0.0246
-8.500 -0.4091 0.01248 0.00722 -0.1163 0.8637 0.0249
-8.250 -0.3820 0.01221 0.00685 -0.1161 0.8461 0.0252
-8.000 -0.3549 0.01195 0.00648 -0.1159 0.8274 0.0254
-7.750 -0.3276 0.01169 0.00611 -0.1157 0.8098 0.0257
-7.500 -0.3001 0.01144 0.00577 -0.1156 0.7942 0.0259
-7.250 -0.2725 0.01121 0.00545 -0.1155 0.7779 0.0261
-7.000 -0.2449 0.01100 0.00514 -0.1154 0.7602 0.0263
-6.750 -0.2171 0.01082 0.00486 -0.1152 0.7424 0.0265
-6.500 -0.1893 0.01065 0.00460 -0.1151 0.7240 0.0266
-6.250 -0.1616 0.01042 0.00427 -0.1150 0.7055 0.0270
-5.750 -0.1057 0.01004 0.00374 -0.1149 0.6722 0.0278
-5.500 -0.0775 0.00990 0.00353 -0.1149 0.6571 0.0283
-5.250 -0.0492 0.00978 0.00335 -0.1148 0.6435 0.0287
-5.000 -0.0209 0.00967 0.00317 -0.1148 0.6317 0.0292
-4.750 0.0077 0.00955 0.00301 -0.1148 0.6201 0.0297
-4.500 0.0362 0.00946 0.00286 -0.1148 0.6088 0.0302
-4.250 0.0647 0.00938 0.00272 -0.1147 0.5971 0.0307
-4.000 0.0934 0.00927 0.00257 -0.1148 0.5875 0.0315
-3.750 0.1219 0.00918 0.00244 -0.1147 0.5760 0.0327
-3.500 0.1505 0.00910 0.00233 -0.1147 0.5630 0.0338
-3.250 0.1791 0.00905 0.00223 -0.1147 0.5500 0.0350
-3.000 0.2076 0.00901 0.00213 -0.1147 0.5369 0.0368
-2.750 0.2359 0.00897 0.00206 -0.1146 0.5210 0.0397
-2.500 0.2642 0.00895 0.00199 -0.1146 0.5027 0.0446
-2.250 0.2923 0.00895 0.00194 -0.1145 0.4836 0.0523
-2.000 0.3205 0.00896 0.00191 -0.1145 0.4672 0.0605
-1.750 0.3485 0.00899 0.00190 -0.1144 0.4485 0.0681
-1.500 0.3763 0.00905 0.00189 -0.1143 0.4265 0.0753
-1.250 0.4043 0.00912 0.00189 -0.1142 0.4084 0.0822
-1.000 0.4325 0.00915 0.00188 -0.1142 0.3957 0.0912
-0.750 0.4611 0.00908 0.00186 -0.1142 0.3864 0.1142
-0.500 0.4894 0.00900 0.00188 -0.1143 0.3768 0.1622
-0.250 0.5179 0.00899 0.00191 -0.1143 0.3673 0.1891
0.000 0.5462 0.00901 0.00195 -0.1143 0.3581 0.2096
0.250 0.5743 0.00905 0.00199 -0.1143 0.3459 0.2301
0.500 0.6027 0.00904 0.00203 -0.1144 0.3364 0.2638
0.750 0.6307 0.00901 0.00210 -0.1144 0.3255 0.3210
1.000 0.6589 0.00901 0.00217 -0.1145 0.3142 0.3713
1.250 0.6868 0.00906 0.00225 -0.1145 0.3031 0.4076
1.500 0.7147 0.00909 0.00234 -0.1144 0.2924 0.4549
1.750 0.7427 0.00910 0.00244 -0.1145 0.2820 0.5068
2.000 0.7703 0.00916 0.00256 -0.1144 0.2706 0.5616
2.250 0.7974 0.00927 0.00272 -0.1142 0.2558 0.6147
2.500 0.8241 0.00947 0.00289 -0.1140 0.2370 0.6458
2.750 0.8500 0.00978 0.00310 -0.1136 0.2130 0.6673
3.000 0.8752 0.01016 0.00335 -0.1131 0.1847 0.6847
3.250 0.8980 0.01082 0.00377 -0.1123 0.1378 0.7019
3.500 0.9196 0.01162 0.00431 -0.1113 0.0833 0.7147
3.750 0.9460 0.01185 0.00453 -0.1110 0.0780 0.7265
4.000 0.9728 0.01204 0.00472 -0.1108 0.0743 0.7376
4.250 0.9990 0.01229 0.00494 -0.1104 0.0693 0.7472
4.500 1.0249 0.01257 0.00519 -0.1100 0.0608 0.7545
4.750 1.0483 0.01311 0.00562 -0.1093 0.0308 0.7646
5.000 1.0741 0.01333 0.00587 -0.1089 0.0293 0.7782
5.250 1.0999 0.01356 0.00613 -0.1085 0.0285 0.7907
5.500 1.1255 0.01380 0.00639 -0.1081 0.0278 0.8032
5.750 1.1505 0.01404 0.00668 -0.1076 0.0271 0.8179
6.000 1.1752 0.01429 0.00699 -0.1070 0.0265 0.8359
6.250 1.1996 0.01450 0.00727 -0.1063 0.0262 0.8580
6.500 1.2217 0.01454 0.00752 -0.1052 0.0259 0.9805
6.750 1.2463 0.01486 0.00784 -0.1047 0.0255 1.0000
7.000 1.2706 0.01519 0.00817 -0.1041 0.0251 1.0000
7.250 1.2945 0.01555 0.00853 -0.1035 0.0247 1.0000
7.500 1.3179 0.01592 0.00891 -0.1028 0.0243 1.0000
7.750 1.3408 0.01632 0.00932 -0.1021 0.0240 1.0000
8.000 1.3629 0.01676 0.00976 -0.1012 0.0237 1.0000
8.250 1.3841 0.01724 0.01027 -0.1003 0.0233 1.0000
8.500 1.4048 0.01773 0.01077 -0.0992 0.0231 1.0000
8.750 1.4259 0.01816 0.01122 -0.0982 0.0229 1.0000
9.000 1.4464 0.01860 0.01167 -0.0972 0.0226 1.0000
9.250 1.4647 0.01905 0.01216 -0.0957 0.0223 1.0000
9.500 1.4818 0.01956 0.01269 -0.0941 0.0221 1.0000
9.750 1.4980 0.02012 0.01328 -0.0924 0.0218 1.0000
10.000 1.5134 0.02072 0.01391 -0.0907 0.0216 1.0000
10.250 1.5281 0.02137 0.01459 -0.0889 0.0214 1.0000
10.500 1.5420 0.02208 0.01534 -0.0872 0.0211 1.0000
10.750 1.5554 0.02284 0.01614 -0.0855 0.0209 1.0000
11.000 1.5681 0.02368 0.01701 -0.0838 0.0207 1.0000
11.250 1.5794 0.02465 0.01803 -0.0821 0.0204 1.0000
11.500 1.5887 0.02581 0.01924 -0.0803 0.0202 1.0000
11.750 1.5956 0.02720 0.02069 -0.0785 0.0200 1.0000
12.000 1.6060 0.02839 0.02194 -0.0771 0.0199 1.0000
12.250 1.6155 0.02971 0.02332 -0.0758 0.0197 1.0000
12.500 1.6242 0.03115 0.02482 -0.0747 0.0196 1.0000
12.750 1.6323 0.03271 0.02644 -0.0736 0.0194 1.0000
13.000 1.6393 0.03444 0.02823 -0.0726 0.0191 1.0000
13.250 1.6451 0.03634 0.03020 -0.0718 0.0189 1.0000
13.500 1.6497 0.03845 0.03238 -0.0710 0.0187 1.0000
13.750 1.6531 0.04077 0.03478 -0.0705 0.0185 1.0000
14.000 1.6549 0.04334 0.03742 -0.0700 0.0184 1.0000
14.250 1.6554 0.04615 0.04031 -0.0697 0.0182 1.0000
14.500 1.6550 0.04914 0.04338 -0.0696 0.0181 1.0000
14.750 1.6534 0.05238 0.04670 -0.0696 0.0179 1.0000
15.000 1.6506 0.05580 0.05022 -0.0697 0.0178 1.0000
15.250 1.6464 0.05952 0.05402 -0.0700 0.0177 1.0000
15.500 1.6412 0.06344 0.05803 -0.0705 0.0175 1.0000
15.750 1.6328 0.06787 0.06256 -0.0711 0.0174 1.0000
16.000 1.6226 0.07264 0.06742 -0.0719 0.0173 1.0000
16.250 1.6106 0.07780 0.07269 -0.0730 0.0172 1.0000
16.500 1.5960 0.08338 0.07837 -0.0742 0.0171 1.0000
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