USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 31 AIRFOIL (usa31-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.88 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa31-il-1000000-n5.txt Download as CSV file: xf-usa31-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 31 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
------ -------- --------- --------- -------- -------- --------
-12.500 0.2808 0.09346 0.09106 -0.1824 0.9285 0.0165
-12.250 0.2904 0.09257 0.09018 -0.1818 0.9248 0.0167
-12.000 0.2981 0.09034 0.08795 -0.1825 0.9214 0.0167
-11.750 0.3134 0.08876 0.08636 -0.1840 0.9188 0.0169
-11.500 0.3224 0.08661 0.08420 -0.1849 0.9159 0.0170
-11.250 0.3263 0.08492 0.08254 -0.1841 0.9112 0.0173
-11.000 0.3338 0.08290 0.08050 -0.1845 0.9064 0.0174
-10.750 0.3429 0.08058 0.07817 -0.1856 0.9022 0.0177
-10.500 0.3468 0.07851 0.07611 -0.1854 0.8957 0.0178
-10.250 0.3544 0.07619 0.07375 -0.1862 0.8887 0.0180
-10.000 0.3595 0.07392 0.07147 -0.1865 0.8803 0.0181
-9.750 0.3656 0.07144 0.06894 -0.1874 0.8710 0.0183
-9.500 0.3700 0.06892 0.06636 -0.1880 0.8588 0.0185
-9.250 0.3542 0.06324 0.06061 -0.1894 0.8450 0.0195
-9.000 0.3554 0.06093 0.05823 -0.1893 0.8317 0.0195
-8.750 0.3593 0.05936 0.05660 -0.1888 0.8188 0.0196
-8.500 0.3543 0.05675 0.05393 -0.1883 0.8075 0.0196
-8.250 0.3540 0.05497 0.05213 -0.1875 0.7966 0.0197
-8.000 0.3506 0.05323 0.05036 -0.1862 0.7866 0.0198
-7.500 0.2008 0.02697 0.02361 -0.1938 0.7634 0.0203
-7.250 0.2043 0.02299 0.01929 -0.1944 0.7534 0.0204
-7.000 0.2153 0.02064 0.01667 -0.1936 0.7433 0.0206
-6.750 0.2273 0.01924 0.01505 -0.1917 0.7338 0.0207
-6.500 0.2397 0.01820 0.01381 -0.1894 0.7223 0.0209
-6.250 0.2522 0.01728 0.01269 -0.1868 0.7109 0.0210
-6.000 0.2629 0.01650 0.01172 -0.1837 0.6982 0.0211
-5.500 0.2787 0.01528 0.01016 -0.1759 0.6720 0.0214
-5.250 0.2890 0.01481 0.00954 -0.1724 0.6611 0.0215
-5.000 0.2995 0.01429 0.00887 -0.1689 0.6505 0.0216
-4.750 0.3143 0.01387 0.00832 -0.1663 0.6417 0.0217
-4.500 0.3282 0.01348 0.00779 -0.1634 0.6327 0.0218
-4.250 0.3453 0.01311 0.00732 -0.1612 0.6257 0.0219
-4.000 0.3632 0.01279 0.00690 -0.1592 0.6192 0.0221
-3.500 0.4005 0.01232 0.00626 -0.1553 0.6068 0.0223
-3.250 0.4202 0.01215 0.00602 -0.1536 0.6004 0.0224
-3.000 0.4390 0.01209 0.00587 -0.1517 0.5942 0.0226
-2.750 0.4591 0.01178 0.00551 -0.1500 0.5897 0.0227
-2.500 0.4794 0.01157 0.00526 -0.1484 0.5838 0.0230
-2.250 0.4994 0.01147 0.00512 -0.1468 0.5781 0.0230
-2.000 0.5194 0.01139 0.00500 -0.1451 0.5727 0.0232
-1.750 0.5411 0.01131 0.00490 -0.1438 0.5671 0.0235
-1.500 0.5617 0.01126 0.00482 -0.1422 0.5613 0.0237
-1.250 0.5812 0.01123 0.00473 -0.1405 0.5556 0.0237
-1.000 0.6039 0.01118 0.00465 -0.1394 0.5503 0.0241
-0.750 0.6245 0.01117 0.00460 -0.1379 0.5429 0.0243
-0.500 0.6443 0.01119 0.00458 -0.1362 0.5367 0.0246
-0.250 0.6662 0.01116 0.00453 -0.1350 0.5308 0.0247
0.000 0.6859 0.01120 0.00452 -0.1333 0.5231 0.0250
0.250 0.7063 0.01123 0.00451 -0.1318 0.5164 0.0253
0.500 0.7279 0.01127 0.00451 -0.1305 0.5094 0.0256
0.750 0.7470 0.01136 0.00455 -0.1288 0.5013 0.0257
1.000 0.7691 0.01140 0.00457 -0.1276 0.4947 0.0259
1.250 0.7883 0.01151 0.00464 -0.1260 0.4864 0.0261
1.500 0.8081 0.01158 0.00466 -0.1244 0.4787 0.0265
1.750 0.8283 0.01167 0.00473 -0.1230 0.4712 0.0272
2.000 0.8480 0.01180 0.00482 -0.1214 0.4639 0.0277
2.250 0.8692 0.01190 0.00490 -0.1202 0.4572 0.0282
2.500 0.8885 0.01207 0.00503 -0.1187 0.4497 0.0288
2.750 0.9094 0.01220 0.00514 -0.1174 0.4441 0.0294
3.000 0.9292 0.01236 0.00528 -0.1160 0.4373 0.0299
3.250 0.9480 0.01257 0.00545 -0.1144 0.4311 0.0305
3.500 0.9695 0.01270 0.00557 -0.1133 0.4267 0.0315
3.750 0.9900 0.01287 0.00573 -0.1120 0.4205 0.0330
4.250 1.0294 0.01327 0.00612 -0.1093 0.4101 0.0425
4.500 1.0496 0.01314 0.00642 -0.1082 0.4055 0.2515
4.750 1.0689 0.01340 0.00669 -0.1069 0.4000 0.2604
5.000 1.0878 0.01369 0.00696 -0.1054 0.3951 0.2679
5.250 1.1090 0.01391 0.00720 -0.1044 0.3908 0.2746
5.500 1.1281 0.01421 0.00750 -0.1031 0.3838 0.2824
5.750 1.1445 0.01462 0.00786 -0.1014 0.3763 0.2856
6.000 1.1647 0.01488 0.00812 -0.1003 0.3711 0.2879
6.250 1.1831 0.01522 0.00844 -0.0989 0.3644 0.2908
6.500 1.2009 0.01559 0.00880 -0.0975 0.3589 0.2928
6.750 1.2196 0.01594 0.00915 -0.0963 0.3518 0.2961
7.000 1.2379 0.01630 0.00951 -0.0950 0.3470 0.2978
7.250 1.2558 0.01670 0.00990 -0.0937 0.3428 0.2993
7.500 1.2753 0.01703 0.01024 -0.0927 0.3385 0.3005
7.750 1.2942 0.01739 0.01061 -0.0916 0.3342 0.3023
8.000 1.3109 0.01786 0.01107 -0.0902 0.3285 0.3034
8.250 1.3275 0.01835 0.01154 -0.0888 0.3227 0.3047
8.500 1.3458 0.01877 0.01197 -0.0877 0.3170 0.3059
8.750 1.3609 0.01936 0.01254 -0.0862 0.3105 0.3068
9.000 1.3775 0.01988 0.01307 -0.0850 0.3052 0.3087
9.250 1.3930 0.02048 0.01365 -0.0836 0.2966 0.3105
9.500 1.4074 0.02114 0.01431 -0.0822 0.2906 0.3118
9.750 1.4243 0.02169 0.01489 -0.0811 0.2859 0.3135
10.000 1.4396 0.02234 0.01553 -0.0799 0.2797 0.3150
10.250 1.4537 0.02307 0.01626 -0.0785 0.2741 0.3167
10.500 1.4655 0.02395 0.01712 -0.0769 0.2636 0.3183
10.750 1.4785 0.02477 0.01793 -0.0755 0.2574 0.3199
11.000 1.4909 0.02565 0.01881 -0.0741 0.2490 0.3213
11.250 1.5019 0.02664 0.01979 -0.0726 0.2424 0.3228
11.500 1.5111 0.02776 0.02087 -0.0710 0.2306 0.3239
11.750 1.5167 0.02916 0.02222 -0.0690 0.2177 0.3248
12.000 1.5261 0.03033 0.02338 -0.0676 0.2102 0.3263
12.250 1.5341 0.03166 0.02470 -0.0661 0.2011 0.3285
12.500 1.5401 0.03313 0.02614 -0.0644 0.1907 0.3301
12.750 1.5486 0.03448 0.02751 -0.0631 0.1851 0.3319
13.000 1.5548 0.03602 0.02904 -0.0617 0.1763 0.3340
13.250 1.5590 0.03776 0.03076 -0.0602 0.1686 0.3352
13.500 1.5657 0.03932 0.03233 -0.0590 0.1618 0.3369
13.750 1.5695 0.04117 0.03418 -0.0576 0.1547 0.3383
14.000 1.5738 0.04302 0.03604 -0.0564 0.1475 0.3397
14.250 1.5798 0.04475 0.03778 -0.0553 0.1425 0.3406
14.500 1.5780 0.04720 0.04020 -0.0539 0.1321 0.3418
14.750 1.5836 0.04904 0.04208 -0.0530 0.1287 0.3433
15.000 1.5821 0.05157 0.04460 -0.0518 0.1190 0.3444
15.250 1.5731 0.05485 0.04784 -0.0503 0.1059 0.3457
15.500 1.5669 0.05793 0.05091 -0.0491 0.0969 0.3469
15.750 1.5627 0.06085 0.05383 -0.0481 0.0906 0.3484
16.000 1.5615 0.06351 0.05652 -0.0473 0.0858 0.3500
16.500 1.5580 0.06910 0.06218 -0.0459 0.0784 0.3539
16.750 1.5579 0.07175 0.06488 -0.0454 0.0758 0.3549
17.000 1.5531 0.07491 0.06807 -0.0448 0.0724 0.3570
17.250 1.5536 0.07753 0.07074 -0.0444 0.0702 0.3584
17.500 1.5507 0.08062 0.07388 -0.0441 0.0663 0.3599
17.750 1.5428 0.08427 0.07755 -0.0437 0.0615 0.3611
18.000 1.5370 0.08770 0.08101 -0.0435 0.0556 0.3625
18.250 1.5034 0.09450 0.08773 -0.0431 0.0372 0.3628
18.500 1.4776 0.10061 0.09383 -0.0431 0.0235 0.3630
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