NASA RC(4)-10 AIRFOIL (rc410-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA RC(4)-10 AIRFOIL (rc410-il) Reynolds number: 500,000 Max Cl/Cd: 73.83 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc410-il-500000-n5.txt Download as CSV file: xf-rc410-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -1.0219 0.03946 0.03602 -0.0258 1.0000 0.0140
-11.500 -1.0199 0.03573 0.03197 -0.0250 1.0000 0.0142
-11.250 -1.0112 0.03295 0.02891 -0.0241 1.0000 0.0143
-11.000 -0.9981 0.03077 0.02647 -0.0232 1.0000 0.0145
-10.750 -0.9821 0.02895 0.02443 -0.0224 1.0000 0.0147
-10.500 -0.9639 0.02741 0.02268 -0.0217 1.0000 0.0148
-10.250 -0.9430 0.02616 0.02113 -0.0211 0.9041 0.0150
-10.000 -0.9284 0.02463 0.01931 -0.0193 0.8734 0.0151
-9.750 -0.9101 0.02336 0.01782 -0.0181 0.8552 0.0153
-9.500 -0.8895 0.02233 0.01662 -0.0172 0.8419 0.0155
-9.000 -0.8446 0.02062 0.01462 -0.0157 0.8217 0.0160
-8.500 -0.7971 0.01914 0.01287 -0.0145 0.8068 0.0164
-8.250 -0.7728 0.01845 0.01206 -0.0139 0.8000 0.0167
-8.000 -0.7480 0.01779 0.01129 -0.0134 0.7940 0.0170
-7.750 -0.7229 0.01717 0.01055 -0.0129 0.7880 0.0173
-7.500 -0.6976 0.01660 0.00986 -0.0124 0.7829 0.0176
-7.250 -0.6718 0.01605 0.00922 -0.0120 0.7780 0.0179
-7.000 -0.6459 0.01555 0.00863 -0.0116 0.7728 0.0182
-6.750 -0.6199 0.01506 0.00804 -0.0111 0.7679 0.0185
-6.500 -0.5941 0.01450 0.00744 -0.0107 0.7632 0.0192
-6.250 -0.5676 0.01407 0.00698 -0.0104 0.7583 0.0198
-6.000 -0.5409 0.01370 0.00654 -0.0101 0.7539 0.0205
-5.750 -0.5142 0.01335 0.00612 -0.0097 0.7500 0.0211
-5.500 -0.4871 0.01299 0.00572 -0.0094 0.7457 0.0218
-5.250 -0.4600 0.01266 0.00534 -0.0091 0.7412 0.0226
-5.000 -0.4331 0.01230 0.00495 -0.0088 0.7369 0.0238
-4.750 -0.4060 0.01200 0.00462 -0.0085 0.7329 0.0254
-4.500 -0.3786 0.01172 0.00432 -0.0083 0.7284 0.0273
-4.250 -0.3514 0.01141 0.00401 -0.0080 0.7242 0.0309
-4.000 -0.3243 0.01113 0.00374 -0.0077 0.7203 0.0369
-3.750 -0.2971 0.01088 0.00352 -0.0075 0.7168 0.0455
-3.500 -0.2695 0.01066 0.00334 -0.0073 0.7127 0.0544
-3.250 -0.2417 0.01048 0.00319 -0.0071 0.7082 0.0622
-3.000 -0.2141 0.01035 0.00304 -0.0069 0.7023 0.0685
-2.750 -0.1861 0.01021 0.00290 -0.0067 0.6939 0.0743
-2.500 -0.1584 0.01010 0.00277 -0.0065 0.6859 0.0802
-2.250 -0.1302 0.01000 0.00267 -0.0064 0.6784 0.0867
-2.000 -0.1023 0.00990 0.00259 -0.0063 0.6713 0.0936
-1.750 -0.0740 0.00983 0.00250 -0.0062 0.6638 0.0994
-1.500 -0.0461 0.00972 0.00239 -0.0060 0.6553 0.1044
-1.250 -0.0179 0.00963 0.00230 -0.0059 0.6476 0.1092
-1.000 0.0102 0.00957 0.00220 -0.0057 0.6386 0.1132
-0.750 0.0383 0.00949 0.00211 -0.0056 0.6285 0.1175
-0.500 0.0663 0.00941 0.00202 -0.0055 0.6183 0.1224
-0.250 0.0944 0.00936 0.00195 -0.0054 0.6074 0.1270
0.000 0.1225 0.00933 0.00188 -0.0052 0.5942 0.1316
0.250 0.1504 0.00928 0.00182 -0.0051 0.5767 0.1380
0.500 0.1783 0.00929 0.00177 -0.0050 0.5554 0.1437
0.750 0.2059 0.00932 0.00172 -0.0048 0.5272 0.1503
1.000 0.2327 0.00950 0.00171 -0.0046 0.4630 0.1595
1.250 0.2565 0.01038 0.00196 -0.0044 0.3018 0.1708
1.500 0.2832 0.01059 0.00206 -0.0043 0.2616 0.1893
1.750 0.3028 0.00958 0.00207 -0.0033 0.2412 0.5703
2.000 0.3245 0.00919 0.00214 -0.0021 0.2268 0.7181
2.250 0.3478 0.00879 0.00234 -0.0006 0.2156 0.9077
2.500 0.3924 0.00900 0.00252 -0.0040 0.2032 0.9520
2.750 0.4315 0.00923 0.00268 -0.0064 0.1926 0.9693
3.000 0.4691 0.00943 0.00282 -0.0084 0.1847 0.9820
3.250 0.5054 0.00964 0.00296 -0.0103 0.1779 0.9883
3.500 0.5404 0.00981 0.00310 -0.0118 0.1724 0.9938
3.750 0.5818 0.01001 0.00324 -0.0148 0.1655 0.9983
4.000 0.6139 0.01019 0.00338 -0.0158 0.1607 1.0000
4.250 0.6391 0.01034 0.00352 -0.0153 0.1569 1.0000
4.500 0.6642 0.01052 0.00366 -0.0147 0.1529 1.0000
4.750 0.6890 0.01073 0.00383 -0.0142 0.1487 1.0000
5.000 0.7141 0.01090 0.00400 -0.0136 0.1455 1.0000
5.250 0.7390 0.01107 0.00417 -0.0131 0.1419 1.0000
5.500 0.7638 0.01128 0.00436 -0.0125 0.1384 1.0000
5.750 0.7884 0.01152 0.00457 -0.0119 0.1350 1.0000
6.000 0.8131 0.01173 0.00479 -0.0113 0.1322 1.0000
6.250 0.8379 0.01193 0.00499 -0.0108 0.1292 1.0000
6.500 0.8624 0.01215 0.00522 -0.0102 0.1259 1.0000
6.750 0.8868 0.01240 0.00546 -0.0096 0.1229 1.0000
7.000 0.9107 0.01270 0.00574 -0.0090 0.1198 1.0000
7.250 0.9353 0.01291 0.00598 -0.0084 0.1175 1.0000
7.500 0.9596 0.01315 0.00625 -0.0078 0.1147 1.0000
7.750 0.9836 0.01342 0.00653 -0.0072 0.1119 1.0000
8.000 1.0072 0.01373 0.00682 -0.0066 0.1092 1.0000
8.250 1.0306 0.01407 0.00717 -0.0059 0.1064 1.0000
8.500 1.0547 0.01432 0.00747 -0.0054 0.1042 1.0000
8.750 1.0786 0.01461 0.00779 -0.0048 0.1016 1.0000
9.000 1.1021 0.01493 0.00813 -0.0042 0.0990 1.0000
9.250 1.1251 0.01530 0.00850 -0.0036 0.0960 1.0000
9.500 1.1481 0.01567 0.00890 -0.0030 0.0936 1.0000
9.750 1.1716 0.01599 0.00927 -0.0024 0.0913 1.0000
10.000 1.1947 0.01634 0.00967 -0.0018 0.0885 1.0000
10.250 1.2172 0.01674 0.01007 -0.0012 0.0856 1.0000
10.500 1.2388 0.01722 0.01056 -0.0006 0.0827 1.0000
10.750 1.2615 0.01759 0.01100 0.0000 0.0808 1.0000
11.000 1.2835 0.01800 0.01147 0.0007 0.0782 1.0000
11.250 1.3049 0.01847 0.01196 0.0013 0.0754 1.0000
11.500 1.3250 0.01902 0.01252 0.0021 0.0725 1.0000
11.750 1.3458 0.01949 0.01306 0.0028 0.0703 1.0000
12.000 1.3660 0.01999 0.01362 0.0036 0.0674 1.0000
12.250 1.3848 0.02059 0.01423 0.0044 0.0639 1.0000
12.500 1.4029 0.02121 0.01489 0.0053 0.0607 1.0000
12.750 1.4197 0.02184 0.01555 0.0064 0.0570 1.0000
13.000 1.4329 0.02265 0.01637 0.0078 0.0535 1.0000
13.250 1.4473 0.02340 0.01720 0.0089 0.0510 1.0000
13.500 1.4607 0.02429 0.01814 0.0100 0.0483 1.0000
13.750 1.4722 0.02538 0.01926 0.0109 0.0456 1.0000
14.000 1.4848 0.02643 0.02039 0.0117 0.0434 1.0000
14.250 1.4959 0.02763 0.02165 0.0125 0.0407 1.0000
14.500 1.5047 0.02909 0.02314 0.0132 0.0381 1.0000
14.750 1.5145 0.03046 0.02461 0.0138 0.0359 1.0000
15.000 1.5219 0.03210 0.02631 0.0144 0.0335 1.0000
15.250 1.5273 0.03395 0.02822 0.0149 0.0314 1.0000
15.500 1.5332 0.03579 0.03015 0.0153 0.0296 1.0000
15.750 1.5362 0.03795 0.03239 0.0156 0.0279 1.0000
16.250 1.5374 0.04294 0.03757 0.0157 0.0250 1.0000
16.500 1.5356 0.04580 0.04054 0.0155 0.0237 1.0000
16.750 1.5303 0.04916 0.04401 0.0150 0.0225 1.0000
17.000 1.5218 0.05306 0.04802 0.0142 0.0216 1.0000
17.250 1.5133 0.05710 0.05220 0.0131 0.0208 1.0000
17.500 1.5011 0.06192 0.05716 0.0114 0.0201 1.0000
17.750 1.4845 0.06774 0.06314 0.0090 0.0195 1.0000
18.000 1.4618 0.07494 0.07052 0.0056 0.0192 1.0000
18.250 1.4307 0.08420 0.07999 0.0008 0.0193 1.0000
18.500 1.3882 0.09599 0.09202 -0.0053 0.0199 1.0000
18.750 1.3372 0.10926 0.10550 -0.0120 0.0208 1.0000
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