NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.34 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rcsc2-il-1000000-n5.txt Download as CSV file: xf-rcsc2-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-SC2 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
------ -------- --------- --------- -------- -------- --------
-16.250 -1.0743 0.08216 0.07950 -0.0329 1.0000 0.0131
-16.000 -1.1334 0.06520 0.06226 -0.0447 1.0000 0.0131
-15.750 -1.1627 0.05531 0.05214 -0.0522 1.0000 0.0131
-15.500 -1.1807 0.04878 0.04543 -0.0566 1.0000 0.0131
-15.250 -1.1925 0.04405 0.04053 -0.0590 1.0000 0.0131
-15.000 -1.2004 0.04044 0.03676 -0.0599 1.0000 0.0131
-14.750 -1.2051 0.03756 0.03374 -0.0598 1.0000 0.0131
-14.500 -1.2073 0.03520 0.03125 -0.0590 1.0000 0.0132
-14.250 -1.2072 0.03325 0.02916 -0.0577 1.0000 0.0132
-14.000 -1.2134 0.03094 0.02669 -0.0554 1.0000 0.0133
-13.750 -1.2147 0.02920 0.02482 -0.0528 1.0000 0.0134
-13.500 -1.2128 0.02787 0.02338 -0.0500 1.0000 0.0135
-13.250 -1.2097 0.02685 0.02227 -0.0467 1.0000 0.0136
-13.000 -1.2046 0.02595 0.02129 -0.0435 1.0000 0.0137
-12.750 -1.1993 0.02513 0.02040 -0.0402 1.0000 0.0137
-12.500 -1.1940 0.02439 0.01958 -0.0366 1.0000 0.0138
-12.250 -1.1790 0.02355 0.01866 -0.0351 0.9993 0.0139
-12.000 -1.1577 0.02270 0.01772 -0.0347 0.9981 0.0140
-11.750 -1.1352 0.02189 0.01683 -0.0345 0.9969 0.0141
-11.500 -1.1116 0.02111 0.01598 -0.0345 0.9959 0.0142
-11.250 -1.0872 0.02037 0.01516 -0.0346 0.9950 0.0143
-11.000 -1.0625 0.01966 0.01438 -0.0346 0.9943 0.0144
-10.750 -1.0397 0.01901 0.01366 -0.0342 0.9929 0.0145
-10.500 -1.0158 0.01838 0.01296 -0.0339 0.9916 0.0146
-10.250 -0.9909 0.01777 0.01228 -0.0338 0.9903 0.0147
-10.000 -0.9651 0.01717 0.01163 -0.0339 0.9891 0.0149
-9.750 -0.9389 0.01660 0.01100 -0.0340 0.9881 0.0150
-9.500 -0.9122 0.01606 0.01039 -0.0342 0.9873 0.0151
-9.250 -0.8849 0.01553 0.00982 -0.0345 0.9865 0.0153
-9.000 -0.8572 0.01503 0.00927 -0.0348 0.9857 0.0154
-8.750 -0.8291 0.01456 0.00874 -0.0352 0.9850 0.0156
-8.250 -0.7771 0.01373 0.00783 -0.0349 0.9823 0.0158
-8.000 -0.7516 0.01336 0.00742 -0.0346 0.9806 0.0160
-7.750 -0.7249 0.01300 0.00703 -0.0346 0.9790 0.0161
-7.500 -0.6984 0.01251 0.00652 -0.0345 0.9774 0.0164
-7.250 -0.6708 0.01212 0.00611 -0.0346 0.9759 0.0167
-7.000 -0.6429 0.01179 0.00576 -0.0348 0.9746 0.0170
-6.750 -0.6149 0.01149 0.00545 -0.0349 0.9733 0.0173
-6.500 -0.5876 0.01123 0.00518 -0.0349 0.9718 0.0177
-6.250 -0.5626 0.01099 0.00494 -0.0344 0.9695 0.0181
-6.000 -0.5364 0.01075 0.00469 -0.0340 0.9672 0.0185
-5.750 -0.5097 0.01051 0.00444 -0.0338 0.9652 0.0189
-5.500 -0.4825 0.01028 0.00420 -0.0337 0.9633 0.0193
-5.250 -0.4557 0.01001 0.00393 -0.0335 0.9614 0.0199
-5.000 -0.4284 0.00978 0.00370 -0.0333 0.9597 0.0205
-4.750 -0.4021 0.00958 0.00351 -0.0330 0.9577 0.0213
-4.500 -0.3761 0.00940 0.00334 -0.0326 0.9551 0.0222
-4.250 -0.3496 0.00923 0.00317 -0.0322 0.9522 0.0230
-4.000 -0.3230 0.00903 0.00297 -0.0319 0.9494 0.0243
-3.750 -0.2961 0.00884 0.00280 -0.0316 0.9468 0.0259
-3.500 -0.2691 0.00868 0.00265 -0.0313 0.9441 0.0274
-3.250 -0.2432 0.00850 0.00250 -0.0308 0.9401 0.0304
-3.000 -0.2168 0.00831 0.00236 -0.0305 0.9364 0.0364
-2.750 -0.1901 0.00809 0.00222 -0.0302 0.9335 0.0499
-2.500 -0.1630 0.00792 0.00210 -0.0299 0.9305 0.0604
-2.250 -0.1372 0.00774 0.00198 -0.0294 0.9236 0.0707
-2.000 -0.1108 0.00754 0.00183 -0.0289 0.9158 0.0847
-1.750 -0.0851 0.00730 0.00170 -0.0283 0.9055 0.1124
-1.500 -0.0594 0.00703 0.00157 -0.0278 0.8947 0.1542
-1.250 -0.0334 0.00680 0.00144 -0.0273 0.8809 0.1922
-1.000 -0.0077 0.00657 0.00133 -0.0267 0.8644 0.2428
-0.750 0.0173 0.00628 0.00123 -0.0261 0.8470 0.3083
-0.500 0.0404 0.00591 0.00112 -0.0251 0.8216 0.4130
-0.250 0.0608 0.00572 0.00104 -0.0235 0.7613 0.5080
0.000 0.0801 0.00574 0.00102 -0.0216 0.6842 0.5882
0.250 0.1006 0.00580 0.00105 -0.0200 0.6145 0.6548
0.500 0.1194 0.00596 0.00113 -0.0182 0.5221 0.7317
0.750 0.1397 0.00619 0.00124 -0.0166 0.4334 0.7880
1.000 0.1622 0.00646 0.00135 -0.0154 0.3579 0.8212
1.500 0.2115 0.00683 0.00155 -0.0138 0.2732 0.8700
1.750 0.2367 0.00703 0.00165 -0.0132 0.2348 0.8859
2.000 0.2611 0.00732 0.00177 -0.0124 0.1831 0.9007
2.250 0.2859 0.00759 0.00191 -0.0117 0.1444 0.9153
2.500 0.3113 0.00782 0.00202 -0.0111 0.1167 0.9265
2.750 0.3376 0.00803 0.00215 -0.0107 0.0956 0.9330
3.000 0.3638 0.00824 0.00228 -0.0103 0.0788 0.9398
3.250 0.3906 0.00843 0.00241 -0.0100 0.0676 0.9454
3.500 0.4178 0.00862 0.00255 -0.0098 0.0587 0.9511
3.750 0.4439 0.00880 0.00269 -0.0094 0.0516 0.9576
4.000 0.4725 0.00902 0.00286 -0.0095 0.0428 0.9619
4.250 0.5000 0.00928 0.00304 -0.0095 0.0321 0.9669
4.500 0.5262 0.00951 0.00322 -0.0091 0.0273 0.9722
4.750 0.5568 0.00974 0.00343 -0.0097 0.0246 0.9749
5.000 0.5867 0.00998 0.00364 -0.0102 0.0226 0.9782
5.250 0.6155 0.01020 0.00386 -0.0104 0.0213 0.9821
5.500 0.6447 0.01044 0.00409 -0.0108 0.0202 0.9848
5.750 0.6757 0.01073 0.00436 -0.0115 0.0192 0.9861
6.000 0.7066 0.01098 0.00461 -0.0123 0.0187 0.9874
6.250 0.7370 0.01124 0.00487 -0.0130 0.0183 0.9888
6.500 0.7667 0.01151 0.00515 -0.0135 0.0179 0.9905
6.750 0.7958 0.01180 0.00544 -0.0139 0.0175 0.9923
7.000 0.8244 0.01210 0.00575 -0.0142 0.0171 0.9942
7.250 0.8553 0.01243 0.00608 -0.0150 0.0168 0.9953
7.500 0.8854 0.01279 0.00645 -0.0157 0.0165 0.9965
7.750 0.9146 0.01319 0.00686 -0.0162 0.0162 0.9978
8.000 0.9430 0.01365 0.00734 -0.0166 0.0159 0.9991
8.250 0.9687 0.01409 0.00782 -0.0164 0.0157 1.0000
8.500 0.9879 0.01441 0.00816 -0.0147 0.0156 1.0000
8.750 1.0072 0.01474 0.00853 -0.0130 0.0155 1.0000
9.000 1.0265 0.01510 0.00892 -0.0114 0.0154 1.0000
9.250 1.0458 0.01549 0.00934 -0.0098 0.0153 1.0000
9.500 1.0650 0.01590 0.00980 -0.0083 0.0152 1.0000
9.750 1.0842 0.01635 0.01028 -0.0067 0.0151 1.0000
10.000 1.1037 0.01681 0.01079 -0.0052 0.0150 1.0000
10.250 1.1232 0.01731 0.01134 -0.0038 0.0149 1.0000
10.500 1.1428 0.01783 0.01191 -0.0025 0.0148 1.0000
10.750 1.1623 0.01838 0.01251 -0.0012 0.0147 1.0000
11.000 1.1815 0.01895 0.01314 0.0002 0.0146 1.0000
11.250 1.2003 0.01956 0.01381 0.0015 0.0146 1.0000
11.500 1.2186 0.02019 0.01450 0.0029 0.0145 1.0000
11.750 1.2364 0.02085 0.01523 0.0044 0.0144 1.0000
12.000 1.2535 0.02155 0.01600 0.0059 0.0143 1.0000
12.250 1.2697 0.02228 0.01679 0.0075 0.0143 1.0000
12.500 1.2845 0.02302 0.01761 0.0094 0.0142 1.0000
12.750 1.2972 0.02380 0.01846 0.0115 0.0142 1.0000
13.000 1.3088 0.02462 0.01938 0.0138 0.0141 1.0000
13.250 1.3196 0.02551 0.02035 0.0160 0.0141 1.0000
13.500 1.3296 0.02647 0.02139 0.0182 0.0140 1.0000
13.750 1.3386 0.02750 0.02251 0.0204 0.0140 1.0000
14.000 1.3465 0.02863 0.02373 0.0226 0.0139 1.0000
14.250 1.3533 0.02985 0.02505 0.0247 0.0139 1.0000
14.500 1.3587 0.03120 0.02651 0.0267 0.0138 1.0000
14.750 1.3629 0.03272 0.02813 0.0286 0.0138 1.0000
15.000 1.3656 0.03439 0.02991 0.0304 0.0138 1.0000
15.250 1.3669 0.03630 0.03193 0.0319 0.0137 1.0000
15.500 1.3662 0.03849 0.03424 0.0331 0.0137 1.0000
15.750 1.3640 0.04101 0.03688 0.0338 0.0137 1.0000
16.000 1.3596 0.04397 0.03996 0.0341 0.0137 1.0000
16.250 1.3530 0.04750 0.04362 0.0336 0.0136 1.0000
16.500 1.3432 0.05180 0.04807 0.0323 0.0136 1.0000
16.750 1.3305 0.05704 0.05346 0.0298 0.0136 1.0000
17.000 1.3126 0.06372 0.06032 0.0259 0.0136 1.0000
17.250 1.2880 0.07232 0.06911 0.0204 0.0136 1.0000
17.500 1.2524 0.08361 0.08062 0.0132 0.0136 1.0000
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Polar data table (+)
Polar graphs
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