NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Reynolds number: 100,000 Max Cl/Cd: 46.11 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc10b3-il-100000-n5.txt Download as CSV file: xf-rc10b3-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-10(B)3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5180 0.11749 0.11221 -0.0098 1.0000 0.0568
-10.250 -0.5180 0.11337 0.10813 -0.0123 1.0000 0.0575
-9.750 -0.5321 0.09877 0.09358 -0.0224 1.0000 0.0386
-9.500 -0.5288 0.09505 0.08988 -0.0231 1.0000 0.0381
-9.250 -0.5289 0.09068 0.08555 -0.0253 1.0000 0.0377
-9.000 -0.5319 0.08585 0.08075 -0.0286 1.0000 0.0373
-8.750 -0.5381 0.08098 0.07590 -0.0317 1.0000 0.0367
-8.500 -0.5469 0.07657 0.07148 -0.0330 1.0000 0.0362
-8.250 -0.5548 0.07217 0.06704 -0.0337 1.0000 0.0356
-8.000 -0.5615 0.06767 0.06244 -0.0337 1.0000 0.0350
-7.500 -0.5937 0.05442 0.04841 -0.0293 1.0000 0.0312
-7.250 -0.5947 0.05161 0.04546 -0.0263 1.0000 0.0310
-7.000 -0.5959 0.04887 0.04256 -0.0228 1.0000 0.0308
-6.750 -0.5967 0.04621 0.03969 -0.0192 1.0000 0.0307
-6.500 -0.5961 0.04358 0.03682 -0.0155 1.0000 0.0306
-6.250 -0.5937 0.04099 0.03393 -0.0118 1.0000 0.0305
-6.000 -0.5891 0.03847 0.03108 -0.0084 1.0000 0.0304
-5.750 -0.5704 0.03541 0.02756 -0.0075 0.9966 0.0305
-5.500 -0.5445 0.03247 0.02407 -0.0077 0.9919 0.0307
-5.250 -0.5161 0.03002 0.02105 -0.0080 0.9872 0.0312
-5.000 -0.4868 0.02835 0.01929 -0.0091 0.9832 0.0327
-4.750 -0.4572 0.02704 0.01778 -0.0098 0.9783 0.0345
-4.500 -0.4243 0.02542 0.01585 -0.0109 0.9746 0.0357
-4.250 -0.3918 0.02393 0.01411 -0.0118 0.9708 0.0368
-4.000 -0.3603 0.02268 0.01264 -0.0124 0.9661 0.0382
-3.750 -0.3269 0.02149 0.01138 -0.0136 0.9624 0.0400
-3.500 -0.2918 0.02068 0.01060 -0.0154 0.9593 0.0440
-3.250 -0.2637 0.02002 0.00984 -0.0155 0.9530 0.0486
-3.000 -0.2324 0.01919 0.00904 -0.0164 0.9485 0.0543
-2.750 -0.1986 0.01850 0.00836 -0.0177 0.9448 0.0658
-2.500 -0.1734 0.01797 0.00788 -0.0172 0.9374 0.0864
-2.250 -0.1422 0.01724 0.00743 -0.0181 0.9326 0.1368
-2.000 -0.1149 0.01604 0.00711 -0.0186 0.9274 0.3179
-1.750 -0.0057 0.01528 0.00832 -0.0322 0.9420 0.9420
-1.500 0.1084 0.01538 0.00812 -0.0493 0.9544 1.0000
-1.250 0.1426 0.01527 0.00787 -0.0510 0.9464 1.0000
-1.000 0.1727 0.01519 0.00768 -0.0517 0.9365 1.0000
-0.750 0.2033 0.01511 0.00749 -0.0524 0.9273 1.0000
-0.500 0.2315 0.01504 0.00734 -0.0526 0.9170 1.0000
-0.250 0.2571 0.01500 0.00724 -0.0523 0.9054 1.0000
0.000 0.2826 0.01495 0.00713 -0.0517 0.8941 1.0000
0.250 0.3079 0.01487 0.00699 -0.0511 0.8830 1.0000
0.500 0.3317 0.01481 0.00689 -0.0501 0.8709 1.0000
0.750 0.3546 0.01477 0.00683 -0.0490 0.8581 1.0000
1.000 0.3778 0.01473 0.00677 -0.0479 0.8457 1.0000
1.250 0.4011 0.01468 0.00670 -0.0467 0.8333 1.0000
1.500 0.4243 0.01462 0.00663 -0.0455 0.8203 1.0000
1.750 0.4473 0.01456 0.00656 -0.0442 0.8066 1.0000
2.000 0.4704 0.01451 0.00650 -0.0429 0.7919 1.0000
2.250 0.4934 0.01448 0.00647 -0.0417 0.7764 1.0000
2.500 0.5165 0.01446 0.00648 -0.0405 0.7597 1.0000
2.750 0.5396 0.01445 0.00649 -0.0393 0.7411 1.0000
3.000 0.5625 0.01442 0.00646 -0.0380 0.7202 1.0000
3.250 0.5854 0.01442 0.00645 -0.0366 0.6969 1.0000
3.500 0.6083 0.01444 0.00646 -0.0353 0.6718 1.0000
3.750 0.6311 0.01451 0.00650 -0.0340 0.6433 1.0000
4.000 0.6534 0.01461 0.00652 -0.0325 0.6083 1.0000
4.250 0.6750 0.01479 0.00659 -0.0310 0.5651 1.0000
4.500 0.6958 0.01509 0.00669 -0.0294 0.5155 1.0000
4.750 0.7155 0.01553 0.00687 -0.0278 0.4604 1.0000
5.000 0.7343 0.01608 0.00715 -0.0261 0.4043 1.0000
5.250 0.7525 0.01671 0.00754 -0.0245 0.3515 1.0000
5.500 0.7706 0.01735 0.00796 -0.0229 0.3036 1.0000
5.750 0.7884 0.01803 0.00843 -0.0214 0.2576 1.0000
6.250 0.8227 0.01951 0.00955 -0.0181 0.1751 1.0000
6.500 0.8390 0.02034 0.01020 -0.0164 0.1431 1.0000
6.750 0.8552 0.02117 0.01092 -0.0147 0.1181 1.0000
7.000 0.8705 0.02206 0.01170 -0.0128 0.1010 1.0000
7.250 0.8860 0.02291 0.01256 -0.0108 0.0897 1.0000
7.500 0.9009 0.02378 0.01346 -0.0088 0.0817 1.0000
7.750 0.9145 0.02473 0.01439 -0.0067 0.0753 1.0000
8.000 0.9293 0.02559 0.01533 -0.0046 0.0699 1.0000
8.250 0.9432 0.02652 0.01631 -0.0025 0.0659 1.0000
8.750 0.9702 0.02862 0.01855 0.0018 0.0596 1.0000
9.000 0.9846 0.02961 0.01964 0.0037 0.0564 1.0000
9.250 0.9981 0.03069 0.02075 0.0057 0.0539 1.0000
9.500 1.0118 0.03210 0.02215 0.0075 0.0521 1.0000
9.750 1.0275 0.03342 0.02367 0.0092 0.0503 1.0000
10.000 1.0418 0.03473 0.02519 0.0110 0.0482 1.0000
10.250 1.0545 0.03603 0.02664 0.0129 0.0461 1.0000
10.500 1.0664 0.03737 0.02808 0.0148 0.0444 1.0000
10.750 1.0787 0.03897 0.02975 0.0165 0.0432 1.0000
11.000 1.0920 0.04111 0.03198 0.0179 0.0421 1.0000
11.250 1.0979 0.04301 0.03423 0.0205 0.0412 1.0000
11.500 1.0992 0.04498 0.03652 0.0235 0.0401 1.0000
11.750 1.0970 0.04697 0.03878 0.0267 0.0391 1.0000
12.000 1.0936 0.04906 0.04112 0.0295 0.0381 1.0000
12.250 1.0888 0.05134 0.04363 0.0321 0.0373 1.0000
12.500 1.0822 0.05394 0.04645 0.0342 0.0367 1.0000
12.750 1.0734 0.05686 0.04960 0.0359 0.0362 1.0000
13.000 1.0624 0.06014 0.05309 0.0371 0.0359 1.0000
13.250 1.0487 0.06386 0.05704 0.0376 0.0356 1.0000
13.500 1.0318 0.06821 0.06161 0.0374 0.0354 1.0000
13.750 1.0107 0.07350 0.06713 0.0360 0.0354 1.0000
14.000 0.9823 0.08046 0.07433 0.0330 0.0355 1.0000
14.250 0.9373 0.09154 0.08571 0.0262 0.0360 1.0000
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Polar data table (+)
Polar graphs
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