NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-10(B)3 AIRFOIL (rc10b3-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.34 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc10b3-il-1000000.txt Download as CSV file: xf-rc10b3-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5754 0.08994 0.08832 -0.0165 1.0000 0.0153
-9.750 -0.5845 0.08408 0.08248 -0.0203 1.0000 0.0155
-9.500 -0.5935 0.07718 0.07559 -0.0274 1.0000 0.0156
-9.250 -0.6084 0.07051 0.06888 -0.0326 1.0000 0.0156
-9.000 -0.6193 0.06579 0.06411 -0.0336 1.0000 0.0157
-8.750 -0.6222 0.06148 0.05973 -0.0343 1.0000 0.0158
-8.500 -0.6217 0.05764 0.05579 -0.0344 1.0000 0.0159
-8.250 -0.6208 0.05415 0.05222 -0.0336 1.0000 0.0161
-8.000 -0.6070 0.04986 0.04778 -0.0354 0.9925 0.0164
-7.750 -0.6493 0.02826 0.02474 -0.0301 0.9726 0.0156
-7.500 -0.6333 0.02610 0.02245 -0.0284 0.9638 0.0146
-7.250 -0.6283 0.02169 0.01747 -0.0246 0.9541 0.0142
-7.000 -0.6131 0.01930 0.01469 -0.0223 0.9463 0.0142
-6.750 -0.5933 0.01781 0.01295 -0.0207 0.9399 0.0144
-6.500 -0.5713 0.01669 0.01163 -0.0195 0.9335 0.0146
-6.250 -0.5487 0.01577 0.01054 -0.0184 0.9278 0.0148
-6.000 -0.5244 0.01497 0.00961 -0.0177 0.9221 0.0149
-5.750 -0.4999 0.01432 0.00884 -0.0169 0.9164 0.0151
-5.500 -0.4751 0.01379 0.00820 -0.0162 0.9112 0.0152
-5.250 -0.4517 0.01253 0.00683 -0.0154 0.9053 0.0154
-5.000 -0.4286 0.01163 0.00586 -0.0144 0.8997 0.0158
-4.750 -0.4037 0.01115 0.00534 -0.0138 0.8944 0.0163
-4.500 -0.3780 0.01080 0.00497 -0.0134 0.8885 0.0170
-4.250 -0.3527 0.01043 0.00456 -0.0128 0.8831 0.0176
-4.000 -0.3269 0.01008 0.00416 -0.0123 0.8775 0.0181
-3.750 -0.3009 0.00978 0.00382 -0.0118 0.8714 0.0187
-3.500 -0.2748 0.00955 0.00353 -0.0114 0.8658 0.0191
-3.250 -0.2496 0.00907 0.00302 -0.0108 0.8595 0.0203
-3.000 -0.2234 0.00883 0.00276 -0.0103 0.8532 0.0215
-2.750 -0.1967 0.00864 0.00254 -0.0100 0.8470 0.0230
-2.500 -0.1703 0.00840 0.00228 -0.0097 0.8402 0.0259
-2.250 -0.1438 0.00821 0.00208 -0.0093 0.8338 0.0316
-2.000 -0.1178 0.00791 0.00190 -0.0089 0.8262 0.0541
-1.750 -0.0917 0.00771 0.00177 -0.0085 0.8188 0.0814
-1.500 -0.0653 0.00748 0.00166 -0.0082 0.8110 0.1165
-1.250 -0.0399 0.00721 0.00155 -0.0077 0.8041 0.1729
-1.000 -0.0166 0.00668 0.00144 -0.0070 0.7964 0.2980
-0.750 0.0006 0.00577 0.00128 -0.0051 0.7888 0.5341
-0.500 0.0092 0.00466 0.00115 -0.0009 0.7802 0.8013
-0.250 0.0419 0.00459 0.00143 -0.0013 0.7722 0.9287
0.000 0.0709 0.00474 0.00156 -0.0013 0.7625 0.9456
0.250 0.1029 0.00493 0.00171 -0.0019 0.7537 0.9539
0.500 0.1407 0.00524 0.00196 -0.0037 0.7441 0.9621
0.750 0.1863 0.00560 0.00228 -0.0073 0.7347 0.9698
1.000 0.2426 0.00599 0.00261 -0.0133 0.7207 0.9758
1.250 0.2842 0.00618 0.00272 -0.0162 0.7047 0.9800
1.500 0.3125 0.00625 0.00274 -0.0163 0.6910 0.9828
1.750 0.3422 0.00630 0.00273 -0.0168 0.6746 0.9845
2.000 0.3756 0.00633 0.00270 -0.0181 0.6568 0.9852
2.250 0.4083 0.00641 0.00267 -0.0193 0.6293 0.9859
2.500 0.4405 0.00651 0.00266 -0.0204 0.5977 0.9867
2.750 0.4720 0.00668 0.00268 -0.0214 0.5599 0.9876
3.000 0.5025 0.00696 0.00272 -0.0223 0.5018 0.9884
3.250 0.5324 0.00728 0.00279 -0.0230 0.4434 0.9894
3.500 0.5623 0.00755 0.00288 -0.0238 0.3984 0.9905
3.750 0.5916 0.00783 0.00298 -0.0244 0.3560 0.9916
4.250 0.6482 0.00841 0.00325 -0.0252 0.2790 0.9940
4.500 0.6779 0.00870 0.00337 -0.0260 0.2418 0.9947
4.750 0.7078 0.00901 0.00352 -0.0269 0.2043 0.9953
5.000 0.7375 0.00936 0.00368 -0.0277 0.1676 0.9959
5.250 0.7672 0.00970 0.00388 -0.0285 0.1364 0.9967
5.500 0.7962 0.01008 0.00410 -0.0292 0.1047 0.9975
5.750 0.8247 0.01047 0.00435 -0.0297 0.0794 0.9983
6.000 0.8531 0.01085 0.00463 -0.0302 0.0616 0.9990
6.250 0.8822 0.01118 0.00490 -0.0309 0.0515 0.9998
6.500 0.9077 0.01144 0.00516 -0.0307 0.0460 1.0000
6.750 0.9302 0.01177 0.00546 -0.0298 0.0416 1.0000
7.000 0.9527 0.01208 0.00579 -0.0290 0.0388 1.0000
7.250 0.9753 0.01232 0.00605 -0.0281 0.0369 1.0000
7.500 0.9971 0.01263 0.00637 -0.0272 0.0348 1.0000
7.750 1.0169 0.01316 0.00693 -0.0258 0.0319 1.0000
8.000 1.0387 0.01339 0.00719 -0.0249 0.0311 1.0000
8.250 1.0597 0.01369 0.00752 -0.0238 0.0300 1.0000
8.500 1.0802 0.01402 0.00787 -0.0225 0.0288 1.0000
8.750 1.0997 0.01441 0.00828 -0.0212 0.0276 1.0000
9.000 1.1157 0.01510 0.00901 -0.0193 0.0258 1.0000
9.250 1.1345 0.01548 0.00943 -0.0178 0.0252 1.0000
9.500 1.1535 0.01582 0.00982 -0.0163 0.0246 1.0000
9.750 1.1715 0.01621 0.01026 -0.0147 0.0238 1.0000
10.000 1.1892 0.01659 0.01067 -0.0131 0.0230 1.0000
10.250 1.2062 0.01700 0.01110 -0.0113 0.0221 1.0000
10.500 1.2197 0.01761 0.01173 -0.0090 0.0212 1.0000
10.750 1.2272 0.01857 0.01278 -0.0057 0.0204 1.0000
11.000 1.2426 0.01894 0.01320 -0.0037 0.0201 1.0000
11.250 1.2566 0.01935 0.01368 -0.0014 0.0196 1.0000
11.500 1.2696 0.01978 0.01416 0.0010 0.0190 1.0000
11.750 1.2815 0.02023 0.01464 0.0035 0.0185 1.0000
12.000 1.2889 0.02065 0.01510 0.0070 0.0180 1.0000
12.250 1.2926 0.02112 0.01561 0.0110 0.0176 1.0000
12.500 1.2963 0.02177 0.01630 0.0147 0.0171 1.0000
12.750 1.2965 0.02280 0.01740 0.0185 0.0166 1.0000
13.000 1.2955 0.02415 0.01885 0.0221 0.0162 1.0000
13.250 1.3072 0.02484 0.01962 0.0238 0.0159 1.0000
13.500 1.3182 0.02566 0.02051 0.0255 0.0156 1.0000
13.750 1.3292 0.02654 0.02147 0.0270 0.0152 1.0000
14.000 1.3395 0.02753 0.02252 0.0283 0.0148 1.0000
14.250 1.3501 0.02854 0.02360 0.0295 0.0144 1.0000
14.500 1.3601 0.02965 0.02477 0.0306 0.0140 1.0000
14.750 1.3676 0.03101 0.02619 0.0317 0.0136 1.0000
15.000 1.3702 0.03288 0.02813 0.0329 0.0133 1.0000
15.250 1.3637 0.03567 0.03104 0.0342 0.0129 1.0000
15.500 1.3614 0.03824 0.03374 0.0349 0.0127 1.0000
15.750 1.3665 0.04019 0.03579 0.0352 0.0125 1.0000
16.000 1.3694 0.04244 0.03816 0.0353 0.0123 1.0000
16.250 1.3703 0.04502 0.04085 0.0353 0.0121 1.0000
16.500 1.3693 0.04794 0.04388 0.0349 0.0119 1.0000
16.750 1.3667 0.05117 0.04723 0.0343 0.0117 1.0000
17.000 1.3629 0.05475 0.05092 0.0333 0.0115 1.0000
17.250 1.3574 0.05876 0.05504 0.0319 0.0113 1.0000
17.500 1.3499 0.06320 0.05960 0.0302 0.0112 1.0000
17.750 1.3402 0.06818 0.06469 0.0280 0.0111 1.0000
18.000 1.3284 0.07367 0.07031 0.0255 0.0110 1.0000
18.250 1.3138 0.07976 0.07652 0.0227 0.0109 1.0000
18.500 1.2962 0.08647 0.08336 0.0194 0.0108 1.0000
18.750 1.2768 0.09367 0.09068 0.0159 0.0108 1.0000
19.000 1.2545 0.10145 0.09859 0.0121 0.0108 1.0000
19.250 1.2314 0.10955 0.10682 0.0081 0.0107 1.0000
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Polar data table (+)
Polar graphs
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