NASA RC(4)-10 AIRFOIL (rc410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA RC(4)-10 AIRFOIL (rc410-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.88 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc410-il-1000000.txt Download as CSV file: xf-rc410-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA RC(4)-10 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
------ -------- --------- --------- -------- -------- --------
-11.500 -1.0268 0.03428 0.03115 -0.0246 1.0000 0.0147
-11.250 -1.0280 0.03016 0.02666 -0.0229 1.0000 0.0149
-11.000 -1.0191 0.02735 0.02359 -0.0216 1.0000 0.0150
-10.750 -1.0039 0.02541 0.02147 -0.0205 1.0000 0.0152
-10.500 -0.9852 0.02396 0.01990 -0.0197 1.0000 0.0153
-10.250 -0.9646 0.02276 0.01860 -0.0190 1.0000 0.0155
-10.000 -0.9429 0.02185 0.01747 -0.0182 0.9124 0.0157
-9.750 -0.9239 0.02104 0.01644 -0.0167 0.8770 0.0159
-9.500 -0.9023 0.02021 0.01543 -0.0157 0.8580 0.0161
-9.000 -0.8562 0.01860 0.01351 -0.0143 0.8335 0.0166
-8.750 -0.8323 0.01785 0.01262 -0.0136 0.8248 0.0169
-8.500 -0.8078 0.01716 0.01180 -0.0130 0.8170 0.0171
-8.250 -0.7828 0.01657 0.01110 -0.0125 0.8104 0.0174
-8.000 -0.7569 0.01609 0.01053 -0.0121 0.8041 0.0177
-7.750 -0.7309 0.01568 0.01001 -0.0117 0.7981 0.0179
-7.500 -0.7072 0.01462 0.00882 -0.0110 0.7927 0.0183
-7.250 -0.6824 0.01384 0.00795 -0.0104 0.7871 0.0187
-7.000 -0.6566 0.01332 0.00737 -0.0100 0.7819 0.0191
-6.750 -0.6302 0.01289 0.00688 -0.0096 0.7773 0.0195
-6.500 -0.6035 0.01248 0.00644 -0.0092 0.7726 0.0199
-6.250 -0.5768 0.01211 0.00601 -0.0089 0.7679 0.0204
-6.000 -0.5499 0.01178 0.00561 -0.0085 0.7634 0.0210
-5.750 -0.5226 0.01145 0.00525 -0.0083 0.7591 0.0214
-5.500 -0.4957 0.01106 0.00481 -0.0079 0.7544 0.0221
-5.250 -0.4690 0.01066 0.00436 -0.0076 0.7500 0.0232
-5.000 -0.4416 0.01039 0.00407 -0.0073 0.7458 0.0244
-4.750 -0.4139 0.01015 0.00381 -0.0071 0.7416 0.0256
-4.500 -0.3866 0.00982 0.00347 -0.0068 0.7374 0.0277
-4.250 -0.3592 0.00958 0.00321 -0.0065 0.7333 0.0304
-4.000 -0.3319 0.00929 0.00294 -0.0062 0.7293 0.0364
-3.750 -0.3047 0.00897 0.00271 -0.0060 0.7244 0.0490
-3.500 -0.2770 0.00880 0.00256 -0.0058 0.7179 0.0592
-3.250 -0.2491 0.00866 0.00244 -0.0056 0.7112 0.0673
-3.000 -0.2209 0.00853 0.00233 -0.0055 0.7050 0.0736
-2.500 -0.1644 0.00835 0.00214 -0.0053 0.6931 0.0844
-2.250 -0.1361 0.00826 0.00207 -0.0052 0.6869 0.0898
-2.000 -0.1076 0.00822 0.00199 -0.0051 0.6805 0.0935
-1.750 -0.0793 0.00810 0.00190 -0.0050 0.6739 0.0992
-1.500 -0.0508 0.00806 0.00186 -0.0050 0.6676 0.1050
-1.250 -0.0220 0.00804 0.00184 -0.0050 0.6606 0.1083
-1.000 0.0060 0.00791 0.00171 -0.0048 0.6528 0.1151
-0.750 0.0345 0.00785 0.00166 -0.0048 0.6457 0.1197
-0.500 0.0631 0.00782 0.00160 -0.0047 0.6375 0.1229
-0.250 0.0914 0.00772 0.00151 -0.0046 0.6284 0.1292
0.000 0.1197 0.00768 0.00145 -0.0045 0.6175 0.1345
0.250 0.1483 0.00766 0.00141 -0.0045 0.6057 0.1387
0.500 0.1765 0.00760 0.00135 -0.0044 0.5925 0.1469
0.750 0.2048 0.00759 0.00132 -0.0044 0.5757 0.1535
1.000 0.2327 0.00759 0.00128 -0.0043 0.5519 0.1643
1.250 0.2603 0.00766 0.00127 -0.0042 0.5107 0.1810
1.500 0.2820 0.00755 0.00134 -0.0036 0.3846 0.4141
1.750 0.2983 0.00704 0.00151 -0.0019 0.2953 0.7383
2.000 0.3186 0.00676 0.00171 0.0002 0.2583 0.9318
2.250 0.3615 0.00705 0.00191 -0.0030 0.2303 0.9706
2.500 0.3994 0.00730 0.00206 -0.0051 0.2130 0.9820
2.750 0.4402 0.00752 0.00219 -0.0079 0.2006 0.9875
3.000 0.4787 0.00773 0.00232 -0.0101 0.1906 0.9927
3.250 0.5184 0.00789 0.00243 -0.0127 0.1832 0.9955
3.500 0.5582 0.00807 0.00253 -0.0153 0.1748 0.9980
3.750 0.5965 0.00821 0.00264 -0.0176 0.1694 0.9999
4.000 0.6229 0.00833 0.00274 -0.0173 0.1649 1.0000
4.250 0.6483 0.00850 0.00286 -0.0168 0.1596 1.0000
4.500 0.6737 0.00864 0.00298 -0.0163 0.1556 1.0000
4.750 0.6992 0.00875 0.00309 -0.0158 0.1522 1.0000
5.000 0.7245 0.00891 0.00321 -0.0153 0.1482 1.0000
5.250 0.7494 0.00913 0.00339 -0.0147 0.1434 1.0000
5.500 0.7747 0.00927 0.00354 -0.0142 0.1409 1.0000
5.750 0.8000 0.00940 0.00367 -0.0137 0.1380 1.0000
6.000 0.8250 0.00957 0.00382 -0.0132 0.1345 1.0000
6.250 0.8498 0.00980 0.00402 -0.0126 0.1307 1.0000
6.500 0.8744 0.01002 0.00425 -0.0120 0.1275 1.0000
6.750 0.8997 0.01016 0.00440 -0.0115 0.1254 1.0000
7.000 0.9247 0.01033 0.00457 -0.0110 0.1225 1.0000
7.250 0.9495 0.01055 0.00477 -0.0104 0.1194 1.0000
7.500 0.9734 0.01086 0.00506 -0.0098 0.1154 1.0000
7.750 0.9983 0.01105 0.00528 -0.0093 0.1135 1.0000
8.000 1.0233 0.01122 0.00547 -0.0088 0.1113 1.0000
8.250 1.0479 0.01144 0.00569 -0.0082 0.1087 1.0000
8.500 1.0721 0.01170 0.00593 -0.0077 0.1056 1.0000
8.750 1.0952 0.01208 0.00630 -0.0070 0.1017 1.0000
9.000 1.1201 0.01225 0.00651 -0.0065 0.1003 1.0000
9.250 1.1446 0.01246 0.00675 -0.0060 0.0979 1.0000
9.500 1.1687 0.01272 0.00701 -0.0054 0.0952 1.0000
9.750 1.1918 0.01308 0.00735 -0.0048 0.0917 1.0000
10.000 1.2152 0.01341 0.00772 -0.0042 0.0892 1.0000
10.250 1.2397 0.01364 0.00798 -0.0038 0.0874 1.0000
10.500 1.2636 0.01392 0.00828 -0.0033 0.0847 1.0000
10.750 1.2867 0.01428 0.00863 -0.0027 0.0816 1.0000
11.000 1.3089 0.01473 0.00908 -0.0021 0.0784 1.0000
11.250 1.3332 0.01496 0.00936 -0.0017 0.0761 1.0000
11.500 1.3562 0.01531 0.00970 -0.0012 0.0724 1.0000
11.750 1.3774 0.01582 0.01019 -0.0005 0.0683 1.0000
12.000 1.4005 0.01613 0.01056 -0.0001 0.0664 1.0000
12.250 1.4224 0.01655 0.01099 0.0005 0.0635 1.0000
12.500 1.4426 0.01710 0.01153 0.0013 0.0599 1.0000
12.750 1.4638 0.01754 0.01202 0.0019 0.0576 1.0000
13.000 1.4840 0.01804 0.01255 0.0027 0.0549 1.0000
13.250 1.5023 0.01868 0.01318 0.0036 0.0516 1.0000
13.500 1.5210 0.01925 0.01379 0.0044 0.0493 1.0000
13.750 1.5376 0.01987 0.01445 0.0055 0.0466 1.0000
14.000 1.5501 0.02069 0.01527 0.0071 0.0435 1.0000
14.250 1.5641 0.02142 0.01606 0.0083 0.0413 1.0000
14.500 1.5762 0.02238 0.01704 0.0094 0.0385 1.0000
14.750 1.5871 0.02349 0.01817 0.0105 0.0358 1.0000
15.000 1.5988 0.02459 0.01932 0.0113 0.0334 1.0000
15.250 1.6068 0.02603 0.02079 0.0122 0.0308 1.0000
15.500 1.6170 0.02733 0.02215 0.0128 0.0288 1.0000
15.750 1.6236 0.02897 0.02384 0.0135 0.0266 1.0000
16.000 1.6297 0.03070 0.02562 0.0141 0.0247 1.0000
16.250 1.6346 0.03256 0.02754 0.0146 0.0229 1.0000
16.500 1.6352 0.03487 0.02991 0.0151 0.0211 1.0000
16.750 1.6381 0.03702 0.03214 0.0154 0.0196 1.0000
17.000 1.6358 0.03973 0.03492 0.0156 0.0182 1.0000
17.250 1.6323 0.04268 0.03796 0.0155 0.0170 1.0000
17.500 1.6281 0.04578 0.04116 0.0153 0.0160 1.0000
17.750 1.6190 0.04956 0.04503 0.0147 0.0151 1.0000
18.000 1.6055 0.05407 0.04965 0.0136 0.0144 1.0000
18.250 1.5935 0.05867 0.05439 0.0122 0.0139 1.0000
18.500 1.5782 0.06407 0.05992 0.0102 0.0135 1.0000
18.750 1.5568 0.07069 0.06670 0.0074 0.0133 1.0000
19.000 1.5263 0.07931 0.07551 0.0032 0.0133 1.0000
19.250 1.4789 0.09157 0.08802 -0.0031 0.0138 1.0000
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