USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 32 AIRFOIL (usa32-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.93 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa32-il-1000000-n5.txt Download as CSV file: xf-usa32-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 32 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
------ -------- --------- --------- -------- -------- --------
-12.250 0.2317 0.08879 0.08606 -0.1726 0.8516 0.0129
-12.000 0.2447 0.08718 0.08443 -0.1738 0.8475 0.0131
-11.750 0.2523 0.08474 0.08199 -0.1749 0.8438 0.0132
-10.750 0.2670 0.07165 0.06883 -0.1815 0.8249 0.0157
-10.500 0.2798 0.07022 0.06739 -0.1824 0.8200 0.0159
-10.250 0.2933 0.06881 0.06595 -0.1835 0.8145 0.0161
-9.750 0.0014 0.02829 0.02493 -0.1923 0.7957 0.0195
-9.500 -0.0011 0.02515 0.02160 -0.1904 0.7902 0.0197
-9.250 0.0025 0.02276 0.01902 -0.1882 0.7830 0.0199
-9.000 0.0152 0.02159 0.01771 -0.1864 0.7745 0.0201
-8.750 0.0213 0.02016 0.01607 -0.1832 0.7628 0.0204
-8.500 0.0232 0.01928 0.01500 -0.1785 0.7452 0.0207
-8.250 -0.0041 0.01912 0.01450 -0.1671 0.6798 0.0207
-8.000 -0.0111 0.01863 0.01374 -0.1603 0.6489 0.0209
-7.750 -0.0069 0.01783 0.01274 -0.1558 0.6379 0.0212
-7.250 0.0146 0.01655 0.01113 -0.1492 0.6248 0.0216
-7.000 0.0307 0.01613 0.01058 -0.1468 0.6202 0.0218
-6.750 0.0447 0.01573 0.01005 -0.1440 0.6146 0.0220
-6.250 0.0741 0.01478 0.00893 -0.1387 0.6054 0.0224
-6.000 0.0922 0.01447 0.00855 -0.1366 0.6009 0.0225
-5.750 0.1100 0.01420 0.00822 -0.1345 0.5964 0.0227
-5.500 0.1273 0.01397 0.00791 -0.1323 0.5921 0.0228
-5.250 0.1462 0.01373 0.00761 -0.1303 0.5889 0.0230
-5.000 0.1673 0.01352 0.00736 -0.1288 0.5866 0.0233
-4.750 0.1878 0.01326 0.00704 -0.1272 0.5840 0.0234
-4.500 0.2087 0.01307 0.00680 -0.1256 0.5812 0.0237
-4.250 0.2292 0.01293 0.00660 -0.1240 0.5778 0.0240
-4.000 0.2493 0.01276 0.00637 -0.1223 0.5750 0.0243
-3.750 0.2691 0.01262 0.00617 -0.1205 0.5719 0.0245
-3.500 0.2906 0.01244 0.00595 -0.1191 0.5695 0.0248
-3.250 0.3125 0.01227 0.00575 -0.1177 0.5673 0.0250
-3.000 0.3343 0.01212 0.00556 -0.1164 0.5649 0.0252
-2.750 0.3560 0.01199 0.00540 -0.1150 0.5621 0.0253
-2.500 0.3772 0.01190 0.00527 -0.1135 0.5587 0.0255
-2.250 0.3977 0.01183 0.00515 -0.1119 0.5552 0.0256
-2.000 0.4188 0.01174 0.00503 -0.1104 0.5523 0.0257
-1.750 0.4410 0.01153 0.00481 -0.1092 0.5499 0.0261
-1.500 0.4632 0.01142 0.00468 -0.1079 0.5469 0.0263
-1.250 0.4850 0.01134 0.00459 -0.1066 0.5434 0.0266
-1.000 0.5063 0.01132 0.00456 -0.1052 0.5394 0.0269
-0.750 0.5262 0.01132 0.00452 -0.1036 0.5347 0.0273
-0.500 0.5496 0.01127 0.00447 -0.1026 0.5306 0.0278
-0.250 0.5718 0.01125 0.00443 -0.1014 0.5255 0.0281
0.000 0.5914 0.01128 0.00443 -0.0998 0.5197 0.0284
0.250 0.6125 0.01131 0.00443 -0.0984 0.5146 0.0288
0.500 0.6337 0.01134 0.00444 -0.0971 0.5076 0.0292
0.750 0.6528 0.01142 0.00448 -0.0953 0.5001 0.0294
1.000 0.6723 0.01152 0.00454 -0.0937 0.4889 0.0297
1.250 0.6905 0.01164 0.00461 -0.0919 0.4800 0.0302
1.500 0.7086 0.01177 0.00469 -0.0901 0.4699 0.0305
1.750 0.7263 0.01193 0.00480 -0.0882 0.4579 0.0314
2.000 0.7443 0.01212 0.00493 -0.0864 0.4486 0.0319
2.250 0.7633 0.01228 0.00506 -0.0848 0.4397 0.0327
2.500 0.7809 0.01249 0.00523 -0.0829 0.4315 0.0340
3.000 0.8188 0.01287 0.00555 -0.0798 0.4170 0.0368
3.500 0.8585 0.01296 0.00590 -0.0772 0.4055 0.1613
3.750 0.8757 0.01321 0.00618 -0.0755 0.3988 0.1884
4.000 0.8960 0.01341 0.00639 -0.0743 0.3932 0.1983
4.250 0.9154 0.01364 0.00662 -0.0730 0.3869 0.2061
4.500 0.9336 0.01393 0.00689 -0.0715 0.3802 0.2161
4.750 0.9545 0.01414 0.00710 -0.0705 0.3750 0.2215
5.000 0.9741 0.01438 0.00736 -0.0693 0.3705 0.2298
5.250 0.9914 0.01474 0.00769 -0.0678 0.3636 0.2352
5.750 1.0332 0.01521 0.00819 -0.0660 0.3564 0.2468
6.250 1.0725 0.01581 0.00883 -0.0639 0.3480 0.2663
6.500 1.0915 0.01615 0.00917 -0.0628 0.3443 0.2726
6.750 1.1123 0.01643 0.00947 -0.0621 0.3407 0.2799
7.000 1.1330 0.01672 0.00980 -0.0613 0.3376 0.2891
7.250 1.1529 0.01706 0.01014 -0.0604 0.3342 0.2959
7.500 1.1717 0.01745 0.01055 -0.0594 0.3304 0.3038
7.750 1.1901 0.01787 0.01099 -0.0584 0.3269 0.3113
8.000 1.2107 0.01821 0.01135 -0.0578 0.3235 0.3169
8.250 1.2304 0.01859 0.01176 -0.0570 0.3195 0.3238
8.500 1.2502 0.01898 0.01216 -0.0563 0.3170 0.3295
8.750 1.2677 0.01947 0.01266 -0.0553 0.3134 0.3333
9.000 1.2855 0.01998 0.01319 -0.0544 0.3100 0.3377
9.250 1.3051 0.02041 0.01364 -0.0538 0.3052 0.3420
9.500 1.3237 0.02089 0.01414 -0.0531 0.3012 0.3461
9.750 1.3420 0.02140 0.01467 -0.0524 0.2985 0.3497
10.000 1.3588 0.02202 0.01531 -0.0515 0.2953 0.3533
10.250 1.3768 0.02257 0.01589 -0.0508 0.2911 0.3573
10.500 1.3957 0.02308 0.01644 -0.0503 0.2879 0.3626
10.750 1.4110 0.02380 0.01716 -0.0493 0.2817 0.3655
11.000 1.4256 0.02461 0.01798 -0.0484 0.2763 0.3693
11.250 1.4433 0.02524 0.01864 -0.0478 0.2716 0.3732
11.500 1.4559 0.02618 0.01957 -0.0467 0.2639 0.3763
11.750 1.4685 0.02715 0.02054 -0.0457 0.2550 0.3799
12.000 1.4791 0.02832 0.02169 -0.0446 0.2443 0.3844
12.250 1.4818 0.03007 0.02336 -0.0429 0.2245 0.3886
12.500 1.4862 0.03177 0.02500 -0.0413 0.2088 0.3933
12.750 1.4748 0.03472 0.02780 -0.0386 0.1812 0.3993
13.000 1.4809 0.03643 0.02952 -0.0376 0.1730 0.4074
13.250 1.4794 0.03882 0.03188 -0.0361 0.1604 0.4165
13.500 1.4906 0.04040 0.03354 -0.0360 0.1561 0.4454
14.000 1.6003 0.04583 0.03999 -0.0567 0.1377 0.9996
14.250 1.6087 0.04824 0.04241 -0.0572 0.1319 1.0000
14.500 1.6062 0.05076 0.04492 -0.0557 0.1223 1.0000
14.750 1.6081 0.05290 0.04709 -0.0546 0.1187 1.0000
15.000 1.5991 0.05614 0.05029 -0.0530 0.1066 1.0000
15.250 1.5952 0.05893 0.05309 -0.0518 0.0997 1.0000
15.500 1.5858 0.06230 0.05645 -0.0504 0.0912 1.0000
16.000 1.5658 0.06937 0.06351 -0.0480 0.0762 1.0000
16.250 1.5653 0.07198 0.06618 -0.0473 0.0751 1.0000
16.500 1.5564 0.07553 0.06975 -0.0464 0.0683 1.0000
16.750 1.5528 0.07855 0.07281 -0.0458 0.0656 1.0000
17.000 1.5433 0.08232 0.07660 -0.0452 0.0600 1.0000
17.250 1.5386 0.08557 0.07989 -0.0448 0.0572 1.0000
17.500 1.5255 0.08989 0.08421 -0.0444 0.0500 1.0000
17.750 1.5169 0.09371 0.08807 -0.0442 0.0458 1.0000
18.000 1.4895 0.10000 0.09433 -0.0440 0.0319 1.0000
18.250 1.4689 0.10558 0.09992 -0.0441 0.0206 1.0000
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