NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.16 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc1064c-il-1000000-n5.txt Download as CSV file: xf-rc1064c-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC10-64C 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
------ -------- --------- --------- -------- -------- --------
-16.000 -1.1667 0.04954 0.04673 -0.0598 0.9454 0.0076
-15.750 -1.1867 0.04376 0.04076 -0.0627 0.9457 0.0076
-15.500 -1.1968 0.04004 0.03689 -0.0633 0.9461 0.0077
-15.250 -1.2014 0.03728 0.03401 -0.0629 0.9464 0.0077
-15.000 -1.2016 0.03514 0.03176 -0.0620 0.9467 0.0078
-14.750 -1.1988 0.03339 0.02990 -0.0607 0.9470 0.0079
-14.500 -1.1937 0.03189 0.02830 -0.0592 0.9473 0.0080
-14.250 -1.1866 0.03059 0.02689 -0.0576 0.9476 0.0082
-14.000 -1.1781 0.02940 0.02560 -0.0559 0.9478 0.0083
-13.750 -1.1681 0.02832 0.02442 -0.0542 0.9480 0.0084
-13.500 -1.1574 0.02732 0.02332 -0.0523 0.9481 0.0086
-13.250 -1.1441 0.02633 0.02223 -0.0509 0.9483 0.0087
-13.000 -1.1288 0.02538 0.02117 -0.0496 0.9484 0.0089
-12.750 -1.1119 0.02452 0.02021 -0.0486 0.9486 0.0091
-12.500 -1.0940 0.02370 0.01930 -0.0476 0.9487 0.0094
-12.250 -1.0754 0.02291 0.01839 -0.0467 0.9488 0.0096
-12.000 -1.0559 0.02217 0.01755 -0.0458 0.9488 0.0097
-11.500 -1.0154 0.02070 0.01587 -0.0443 0.9485 0.0100
-11.250 -0.9942 0.02003 0.01510 -0.0436 0.9484 0.0101
-11.000 -0.9749 0.01906 0.01401 -0.0426 0.9480 0.0103
-10.750 -0.9555 0.01809 0.01292 -0.0417 0.9474 0.0106
-10.500 -0.9334 0.01743 0.01219 -0.0411 0.9467 0.0109
-10.250 -0.9099 0.01696 0.01167 -0.0406 0.9457 0.0112
-10.000 -0.8860 0.01654 0.01119 -0.0402 0.9448 0.0114
-9.750 -0.8622 0.01607 0.01067 -0.0398 0.9441 0.0117
-9.500 -0.8384 0.01559 0.01012 -0.0393 0.9433 0.0120
-9.250 -0.8144 0.01512 0.00958 -0.0389 0.9421 0.0123
-9.000 -0.7901 0.01467 0.00906 -0.0384 0.9413 0.0126
-8.750 -0.7655 0.01424 0.00858 -0.0381 0.9405 0.0128
-8.500 -0.7407 0.01384 0.00811 -0.0377 0.9397 0.0131
-8.250 -0.7159 0.01348 0.00770 -0.0373 0.9385 0.0134
-8.000 -0.6912 0.01318 0.00735 -0.0368 0.9369 0.0136
-7.750 -0.6661 0.01293 0.00705 -0.0364 0.9350 0.0138
-7.500 -0.6426 0.01242 0.00648 -0.0358 0.9334 0.0142
-7.250 -0.6181 0.01202 0.00604 -0.0353 0.9321 0.0147
-7.000 -0.5931 0.01172 0.00569 -0.0348 0.9309 0.0151
-6.750 -0.5678 0.01142 0.00538 -0.0344 0.9295 0.0155
-6.500 -0.5424 0.01115 0.00509 -0.0340 0.9280 0.0160
-6.250 -0.5170 0.01093 0.00485 -0.0336 0.9261 0.0165
-6.000 -0.4919 0.01078 0.00467 -0.0331 0.9238 0.0170
-5.750 -0.4664 0.01054 0.00440 -0.0327 0.9213 0.0175
-5.500 -0.4408 0.01035 0.00420 -0.0323 0.9185 0.0180
-5.250 -0.4153 0.01015 0.00398 -0.0318 0.9164 0.0191
-5.000 -0.3893 0.00987 0.00371 -0.0315 0.9140 0.0204
-4.750 -0.3632 0.00965 0.00350 -0.0312 0.9115 0.0218
-4.250 -0.3103 0.00918 0.00307 -0.0307 0.9059 0.0269
-4.000 -0.2833 0.00893 0.00286 -0.0306 0.8998 0.0317
-3.750 -0.2557 0.00862 0.00262 -0.0307 0.8729 0.0388
-3.500 -0.2305 0.00833 0.00234 -0.0300 0.8651 0.0478
-3.000 -0.1825 0.00786 0.00182 -0.0282 0.8500 0.0688
-2.750 -0.1571 0.00775 0.00170 -0.0276 0.8429 0.0792
-2.500 -0.1308 0.00762 0.00161 -0.0273 0.8350 0.0936
-2.250 -0.1047 0.00749 0.00152 -0.0270 0.8278 0.1143
-2.000 -0.0785 0.00731 0.00146 -0.0267 0.8199 0.1485
-1.750 -0.0506 0.00733 0.00156 -0.0267 0.8106 0.1796
-1.500 -0.0234 0.00733 0.00153 -0.0265 0.7964 0.1851
-1.250 0.0032 0.00734 0.00148 -0.0262 0.7789 0.1883
-1.000 0.0298 0.00740 0.00145 -0.0258 0.7609 0.1911
-0.750 0.0556 0.00737 0.00137 -0.0253 0.7430 0.1931
-0.500 0.0819 0.00736 0.00132 -0.0250 0.7265 0.1950
-0.250 0.1083 0.00737 0.00128 -0.0247 0.7099 0.1964
0.000 0.1342 0.00742 0.00124 -0.0242 0.6862 0.1978
0.250 0.1596 0.00750 0.00122 -0.0236 0.6584 0.1995
0.500 0.1858 0.00756 0.00122 -0.0233 0.6361 0.2005
0.750 0.2115 0.00760 0.00119 -0.0228 0.6112 0.2030
1.000 0.2365 0.00767 0.00117 -0.0223 0.5795 0.2059
1.250 0.2626 0.00774 0.00118 -0.0219 0.5565 0.2073
1.500 0.2872 0.00792 0.00122 -0.0213 0.5117 0.2080
1.750 0.3096 0.00831 0.00131 -0.0203 0.4355 0.2082
2.000 0.3317 0.00876 0.00144 -0.0192 0.3462 0.2084
2.250 0.3550 0.00914 0.00157 -0.0185 0.2795 0.2086
2.500 0.3792 0.00946 0.00170 -0.0179 0.2294 0.2088
2.750 0.4042 0.00971 0.00182 -0.0174 0.1892 0.2090
3.000 0.4296 0.00993 0.00194 -0.0170 0.1612 0.2092
3.250 0.4545 0.01020 0.00209 -0.0166 0.1284 0.2095
3.500 0.4800 0.01041 0.00223 -0.0162 0.1060 0.2098
3.750 0.5055 0.01062 0.00237 -0.0158 0.0871 0.2102
4.250 0.5568 0.01102 0.00269 -0.0152 0.0598 0.2116
4.500 0.5823 0.01123 0.00286 -0.0148 0.0495 0.2128
4.750 0.6079 0.01142 0.00305 -0.0145 0.0429 0.2146
5.000 0.6339 0.01157 0.00324 -0.0142 0.0404 0.2168
5.250 0.6596 0.01175 0.00343 -0.0139 0.0376 0.2188
5.500 0.6849 0.01195 0.00366 -0.0135 0.0341 0.2281
5.750 0.7106 0.01212 0.00389 -0.0132 0.0325 0.2544
6.000 0.7363 0.01229 0.00410 -0.0129 0.0314 0.2591
6.250 0.7617 0.01249 0.00433 -0.0125 0.0301 0.2652
6.500 0.7869 0.01269 0.00458 -0.0122 0.0286 0.2745
6.750 0.8114 0.01286 0.00486 -0.0117 0.0272 0.3245
7.000 0.8271 0.01190 0.00519 -0.0099 0.0258 0.7981
7.250 0.8505 0.01205 0.00550 -0.0091 0.0251 0.8380
7.500 0.8743 0.01221 0.00578 -0.0084 0.0245 0.8657
7.750 0.8975 0.01240 0.00609 -0.0075 0.0237 0.8943
8.000 0.9206 0.01263 0.00642 -0.0067 0.0228 0.9165
8.250 0.9439 0.01291 0.00676 -0.0059 0.0220 0.9333
8.500 0.9679 0.01323 0.00713 -0.0053 0.0212 0.9499
8.750 0.9932 0.01365 0.00758 -0.0051 0.0202 0.9639
9.000 1.0196 0.01412 0.00810 -0.0052 0.0194 0.9747
9.250 1.0471 0.01445 0.00848 -0.0056 0.0190 0.9833
9.500 1.0752 0.01481 0.00889 -0.0061 0.0183 0.9891
9.750 1.1019 0.01517 0.00928 -0.0063 0.0175 0.9942
10.000 1.1298 0.01557 0.00970 -0.0068 0.0167 0.9982
10.250 1.1529 0.01598 0.01013 -0.0063 0.0160 1.0000
10.500 1.1719 0.01646 0.01064 -0.0050 0.0153 1.0000
10.750 1.1910 0.01696 0.01118 -0.0037 0.0148 1.0000
11.000 1.2110 0.01738 0.01166 -0.0026 0.0145 1.0000
11.250 1.2307 0.01783 0.01216 -0.0014 0.0142 1.0000
11.500 1.2503 0.01828 0.01267 -0.0003 0.0137 1.0000
11.750 1.2695 0.01875 0.01318 0.0008 0.0131 1.0000
12.000 1.2884 0.01923 0.01369 0.0020 0.0125 1.0000
12.250 1.3061 0.01977 0.01427 0.0033 0.0119 1.0000
12.500 1.3207 0.02042 0.01497 0.0051 0.0113 1.0000
12.750 1.3357 0.02100 0.01561 0.0069 0.0110 1.0000
13.000 1.3503 0.02161 0.01629 0.0086 0.0107 1.0000
13.250 1.3645 0.02226 0.01702 0.0103 0.0103 1.0000
13.500 1.3781 0.02297 0.01780 0.0120 0.0099 1.0000
13.750 1.3910 0.02376 0.01866 0.0136 0.0095 1.0000
14.000 1.4031 0.02461 0.01956 0.0152 0.0090 1.0000
14.250 1.4140 0.02556 0.02058 0.0168 0.0086 1.0000
14.500 1.4231 0.02666 0.02175 0.0186 0.0082 1.0000
14.750 1.4326 0.02773 0.02292 0.0202 0.0080 1.0000
15.000 1.4409 0.02892 0.02421 0.0217 0.0078 1.0000
15.250 1.4482 0.03025 0.02563 0.0231 0.0075 1.0000
15.500 1.4544 0.03173 0.02719 0.0244 0.0072 1.0000
15.750 1.4593 0.03337 0.02892 0.0256 0.0069 1.0000
16.000 1.4627 0.03523 0.03088 0.0266 0.0066 1.0000
16.250 1.4642 0.03733 0.03308 0.0274 0.0063 1.0000
16.500 1.4635 0.03980 0.03565 0.0279 0.0060 1.0000
16.750 1.4602 0.04265 0.03862 0.0282 0.0058 1.0000
17.000 1.4570 0.04566 0.04175 0.0281 0.0057 1.0000
17.250 1.4519 0.04907 0.04529 0.0275 0.0056 1.0000
17.500 1.4439 0.05302 0.04938 0.0265 0.0056 1.0000
17.750 1.4332 0.05763 0.05413 0.0249 0.0055 1.0000
18.000 1.4189 0.06308 0.05973 0.0226 0.0054 1.0000
18.250 1.3995 0.06967 0.06648 0.0194 0.0054 1.0000
18.500 1.3741 0.07775 0.07474 0.0150 0.0054 1.0000
18.750 1.3372 0.08836 0.08555 0.0092 0.0055 1.0000
19.000 1.2747 0.10456 0.10200 0.0003 0.0057 1.0000
19.250 1.1774 0.12833 0.12608 -0.0123 0.0062 1.0000
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