NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-12(B)3 AIRFOIL (rc12b3-il) Reynolds number: 500,000 Max Cl/Cd: 69.29 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc12b3-il-500000-n5.txt Download as CSV file: xf-rc12b3-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-12(B)3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9507 0.05356 0.05062 -0.0542 1.0000 0.0138
-13.750 -0.9835 0.04626 0.04304 -0.0573 1.0000 0.0138
-13.500 -1.0030 0.04206 0.03859 -0.0563 1.0000 0.0138
-13.250 -1.0153 0.03897 0.03527 -0.0540 1.0000 0.0139
-13.000 -1.0220 0.03651 0.03258 -0.0512 1.0000 0.0140
-12.750 -1.0239 0.03450 0.03035 -0.0484 1.0000 0.0141
-12.500 -1.0272 0.03246 0.02813 -0.0449 1.0000 0.0142
-12.250 -1.0242 0.03084 0.02636 -0.0420 1.0000 0.0144
-12.000 -1.0142 0.02956 0.02497 -0.0400 1.0000 0.0146
-11.750 -0.9952 0.02838 0.02366 -0.0397 0.9811 0.0149
-11.500 -0.9758 0.02728 0.02243 -0.0391 0.9697 0.0151
-11.250 -0.9583 0.02622 0.02122 -0.0380 0.9594 0.0154
-11.000 -0.9420 0.02521 0.02006 -0.0365 0.9503 0.0156
-10.750 -0.9258 0.02427 0.01895 -0.0347 0.9424 0.0158
-10.500 -0.9087 0.02334 0.01787 -0.0332 0.9351 0.0161
-10.250 -0.8911 0.02247 0.01684 -0.0316 0.9287 0.0164
-10.000 -0.8720 0.02162 0.01584 -0.0302 0.9228 0.0167
-9.750 -0.8523 0.02083 0.01488 -0.0290 0.9171 0.0170
-9.500 -0.8321 0.02011 0.01401 -0.0277 0.9123 0.0173
-9.250 -0.8101 0.01943 0.01320 -0.0268 0.9070 0.0175
-9.000 -0.7893 0.01865 0.01231 -0.0256 0.9018 0.0179
-8.750 -0.7680 0.01800 0.01157 -0.0246 0.8974 0.0184
-8.500 -0.7443 0.01749 0.01101 -0.0240 0.8923 0.0189
-8.250 -0.7206 0.01703 0.01048 -0.0233 0.8874 0.0194
-8.000 -0.6970 0.01657 0.00994 -0.0225 0.8831 0.0200
-7.750 -0.6727 0.01608 0.00937 -0.0220 0.8784 0.0206
-7.500 -0.6483 0.01561 0.00881 -0.0213 0.8733 0.0211
-7.250 -0.6239 0.01519 0.00829 -0.0207 0.8689 0.0216
-7.000 -0.5997 0.01469 0.00773 -0.0200 0.8645 0.0223
-6.750 -0.5748 0.01426 0.00728 -0.0196 0.8594 0.0232
-6.500 -0.5496 0.01391 0.00688 -0.0191 0.8548 0.0242
-6.250 -0.5244 0.01358 0.00649 -0.0186 0.8506 0.0252
-6.000 -0.4983 0.01328 0.00614 -0.0182 0.8455 0.0265
-5.750 -0.4730 0.01292 0.00576 -0.0178 0.8405 0.0280
-5.500 -0.4474 0.01263 0.00544 -0.0173 0.8361 0.0298
-5.250 -0.4212 0.01237 0.00514 -0.0170 0.8312 0.0317
-5.000 -0.3951 0.01210 0.00484 -0.0167 0.8260 0.0336
-4.750 -0.3692 0.01184 0.00457 -0.0163 0.8213 0.0363
-4.500 -0.3428 0.01163 0.00432 -0.0160 0.8164 0.0391
-4.250 -0.3165 0.01139 0.00409 -0.0157 0.8110 0.0425
-4.000 -0.2902 0.01120 0.00388 -0.0154 0.8059 0.0466
-3.750 -0.2637 0.01100 0.00367 -0.0151 0.8008 0.0506
-3.500 -0.2372 0.01081 0.00349 -0.0148 0.7950 0.0557
-3.250 -0.2107 0.01065 0.00331 -0.0145 0.7897 0.0611
-3.000 -0.1840 0.01048 0.00315 -0.0143 0.7839 0.0680
-2.750 -0.1574 0.01031 0.00300 -0.0141 0.7778 0.0749
-2.500 -0.1308 0.01018 0.00285 -0.0138 0.7722 0.0823
-2.250 -0.1041 0.01002 0.00272 -0.0136 0.7657 0.0919
-2.000 -0.0776 0.00988 0.00259 -0.0133 0.7593 0.1018
-1.750 -0.0509 0.00974 0.00249 -0.0131 0.7526 0.1152
-1.500 -0.0245 0.00959 0.00238 -0.0128 0.7453 0.1325
-1.250 0.0017 0.00944 0.00228 -0.0125 0.7382 0.1551
-1.000 0.0277 0.00925 0.00219 -0.0121 0.7304 0.1861
-0.500 0.0754 0.00857 0.00201 -0.0108 0.7150 0.3414
-0.250 0.1258 0.00697 0.00245 -0.0157 0.7079 0.8907
0.250 0.1688 0.00734 0.00273 -0.0122 0.6901 0.9311
0.500 0.2070 0.00764 0.00295 -0.0142 0.6794 0.9379
0.750 0.2332 0.00782 0.00307 -0.0137 0.6680 0.9462
1.000 0.2772 0.00810 0.00329 -0.0170 0.6560 0.9506
1.250 0.3059 0.00836 0.00349 -0.0170 0.6445 0.9593
1.500 0.3562 0.00865 0.00371 -0.0218 0.6305 0.9632
1.750 0.3906 0.00878 0.00378 -0.0232 0.6162 0.9661
2.000 0.4190 0.00885 0.00378 -0.0235 0.6014 0.9679
2.250 0.4450 0.00894 0.00379 -0.0232 0.5827 0.9699
2.750 0.4980 0.00919 0.00384 -0.0229 0.5387 0.9728
3.000 0.5280 0.00930 0.00388 -0.0236 0.5170 0.9734
3.250 0.5580 0.00945 0.00394 -0.0242 0.4956 0.9742
3.500 0.5876 0.00960 0.00401 -0.0249 0.4740 0.9750
3.750 0.6158 0.00982 0.00410 -0.0252 0.4469 0.9759
4.250 0.6706 0.01030 0.00435 -0.0257 0.3906 0.9779
4.500 0.6976 0.01054 0.00450 -0.0258 0.3669 0.9792
4.750 0.7233 0.01080 0.00467 -0.0257 0.3435 0.9806
5.000 0.7475 0.01106 0.00484 -0.0252 0.3214 0.9819
5.250 0.7690 0.01136 0.00504 -0.0242 0.2981 0.9836
5.500 0.7968 0.01165 0.00523 -0.0246 0.2738 0.9843
5.750 0.8246 0.01197 0.00545 -0.0251 0.2497 0.9850
6.000 0.8514 0.01230 0.00568 -0.0253 0.2252 0.9857
6.250 0.8773 0.01268 0.00595 -0.0254 0.2013 0.9865
6.500 0.9028 0.01303 0.00622 -0.0254 0.1800 0.9873
6.750 0.9278 0.01342 0.00652 -0.0253 0.1604 0.9882
7.000 0.9528 0.01382 0.00684 -0.0252 0.1427 0.9894
7.250 0.9770 0.01422 0.00717 -0.0250 0.1261 0.9905
7.500 0.9997 0.01465 0.00754 -0.0245 0.1102 0.9916
7.750 1.0217 0.01508 0.00792 -0.0238 0.0970 0.9927
8.000 1.0430 0.01552 0.00832 -0.0230 0.0860 0.9938
8.250 1.0678 0.01596 0.00872 -0.0230 0.0763 0.9945
8.500 1.0920 0.01643 0.00917 -0.0229 0.0673 0.9954
8.750 1.1151 0.01687 0.00960 -0.0226 0.0598 0.9962
9.000 1.1372 0.01736 0.01008 -0.0221 0.0534 0.9970
9.250 1.1586 0.01788 0.01060 -0.0215 0.0479 0.9979
9.500 1.1801 0.01836 0.01111 -0.0209 0.0440 0.9988
9.750 1.2017 0.01893 0.01168 -0.0204 0.0399 0.9998
10.000 1.2153 0.01946 0.01223 -0.0182 0.0371 1.0000
10.250 1.2247 0.01993 0.01275 -0.0152 0.0349 1.0000
10.500 1.2262 0.02042 0.01327 -0.0107 0.0331 1.0000
10.750 1.2262 0.02099 0.01386 -0.0061 0.0312 1.0000
11.000 1.2302 0.02153 0.01446 -0.0023 0.0299 1.0000
11.250 1.2351 0.02212 0.01510 0.0012 0.0284 1.0000
11.500 1.2397 0.02279 0.01581 0.0045 0.0271 1.0000
11.750 1.2437 0.02356 0.01661 0.0078 0.0258 1.0000
12.000 1.2479 0.02438 0.01747 0.0109 0.0247 1.0000
12.250 1.2540 0.02514 0.01831 0.0137 0.0238 1.0000
12.500 1.2598 0.02597 0.01922 0.0163 0.0228 1.0000
12.750 1.2651 0.02691 0.02020 0.0188 0.0218 1.0000
13.000 1.2695 0.02796 0.02129 0.0213 0.0208 1.0000
13.250 1.2731 0.02915 0.02253 0.0237 0.0200 1.0000
13.500 1.2791 0.03025 0.02371 0.0257 0.0193 1.0000
13.750 1.2844 0.03146 0.02500 0.0275 0.0186 1.0000
14.000 1.2893 0.03278 0.02640 0.0293 0.0179 1.0000
14.250 1.2934 0.03424 0.02792 0.0309 0.0172 1.0000
14.500 1.2962 0.03588 0.02962 0.0323 0.0166 1.0000
14.750 1.2976 0.03775 0.03155 0.0337 0.0160 1.0000
15.000 1.3015 0.03949 0.03340 0.0347 0.0155 1.0000
15.250 1.3046 0.04139 0.03539 0.0355 0.0149 1.0000
15.500 1.3069 0.04345 0.03754 0.0362 0.0144 1.0000
15.750 1.3084 0.04572 0.03990 0.0367 0.0138 1.0000
16.000 1.3085 0.04826 0.04251 0.0370 0.0133 1.0000
16.250 1.3062 0.05117 0.04552 0.0370 0.0129 1.0000
16.500 1.3038 0.05422 0.04867 0.0369 0.0125 1.0000
16.750 1.3021 0.05733 0.05190 0.0365 0.0122 1.0000
17.000 1.2991 0.06070 0.05539 0.0360 0.0119 1.0000
17.250 1.2947 0.06434 0.05914 0.0352 0.0116 1.0000
17.500 1.2891 0.06829 0.06321 0.0342 0.0113 1.0000
17.750 1.2822 0.07254 0.06757 0.0329 0.0111 1.0000
18.000 1.2738 0.07710 0.07225 0.0314 0.0108 1.0000
18.250 1.2639 0.08201 0.07727 0.0297 0.0106 1.0000
18.500 1.2525 0.08726 0.08263 0.0277 0.0105 1.0000
18.750 1.2395 0.09289 0.08838 0.0255 0.0103 1.0000
19.000 1.2250 0.09882 0.09443 0.0230 0.0102 1.0000
19.250 1.2094 0.10509 0.10081 0.0204 0.0101 1.0000
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Polar data table (+)
Polar graphs
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