NASA RC(4)-10 AIRFOIL (rc410-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA RC(4)-10 AIRFOIL (rc410-il) Reynolds number: 500,000 Max Cl/Cd: 69.93 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc410-il-500000.txt Download as CSV file: xf-rc410-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5792 0.10641 0.10427 0.0141 1.0000 0.0319
-9.750 -0.8373 0.03823 0.03490 -0.0244 1.0000 0.0221
-9.500 -0.8366 0.03322 0.02937 -0.0234 1.0000 0.0221
-9.250 -0.8262 0.02979 0.02558 -0.0224 1.0000 0.0222
-9.000 -0.8099 0.02729 0.02282 -0.0217 1.0000 0.0224
-8.750 -0.7852 0.02540 0.02068 -0.0222 0.9382 0.0227
-8.500 -0.7675 0.02430 0.01935 -0.0205 0.9050 0.0231
-8.250 -0.7476 0.02325 0.01808 -0.0193 0.8862 0.0236
-8.000 -0.7266 0.02207 0.01666 -0.0182 0.8726 0.0240
-7.750 -0.7049 0.02082 0.01515 -0.0172 0.8616 0.0244
-7.500 -0.6816 0.01968 0.01378 -0.0164 0.8523 0.0248
-7.250 -0.6579 0.01871 0.01259 -0.0156 0.8446 0.0252
-7.000 -0.6328 0.01785 0.01156 -0.0150 0.8371 0.0256
-6.750 -0.6075 0.01717 0.01071 -0.0144 0.8303 0.0259
-6.500 -0.5835 0.01594 0.00934 -0.0137 0.8240 0.0266
-6.250 -0.5583 0.01519 0.00855 -0.0132 0.8175 0.0273
-6.000 -0.5326 0.01469 0.00796 -0.0126 0.8119 0.0282
-5.750 -0.5059 0.01421 0.00744 -0.0123 0.8062 0.0293
-5.500 -0.4793 0.01380 0.00694 -0.0119 0.8007 0.0305
-5.000 -0.4272 0.01271 0.00578 -0.0110 0.7907 0.0336
-4.750 -0.4003 0.01235 0.00538 -0.0106 0.7854 0.0357
-4.500 -0.3742 0.01191 0.00491 -0.0101 0.7807 0.0390
-4.250 -0.3471 0.01156 0.00456 -0.0097 0.7758 0.0444
-4.000 -0.3202 0.01122 0.00429 -0.0094 0.7710 0.0547
-3.750 -0.2926 0.01106 0.00417 -0.0092 0.7666 0.0665
-3.500 -0.2648 0.01098 0.00409 -0.0090 0.7625 0.0753
-3.250 -0.2361 0.01097 0.00405 -0.0090 0.7576 0.0816
-3.000 -0.2086 0.01081 0.00393 -0.0088 0.7517 0.0884
-2.750 -0.1804 0.01082 0.00386 -0.0086 0.7449 0.0937
-2.500 -0.1529 0.01061 0.00369 -0.0083 0.7376 0.0999
-2.250 -0.1249 0.01061 0.00365 -0.0081 0.7318 0.1057
-2.000 -0.0969 0.01046 0.00352 -0.0080 0.7252 0.1119
-1.750 -0.0688 0.01038 0.00345 -0.0078 0.7192 0.1179
-1.500 -0.0407 0.01033 0.00334 -0.0076 0.7134 0.1224
-1.250 -0.0134 0.01006 0.00310 -0.0074 0.7061 0.1280
-1.000 0.0144 0.00994 0.00296 -0.0071 0.7000 0.1334
-0.750 0.0427 0.00986 0.00287 -0.0070 0.6935 0.1382
-0.500 0.0701 0.00963 0.00266 -0.0067 0.6862 0.1445
-0.250 0.0980 0.00952 0.00255 -0.0065 0.6788 0.1509
0.000 0.1259 0.00937 0.00241 -0.0064 0.6705 0.1578
0.250 0.1537 0.00924 0.00229 -0.0062 0.6626 0.1662
0.500 0.1815 0.00909 0.00217 -0.0059 0.6528 0.1767
0.750 0.2092 0.00893 0.00207 -0.0058 0.6414 0.1937
1.000 0.2301 0.00776 0.00190 -0.0048 0.6301 0.5221
1.250 0.2465 0.00651 0.00199 -0.0016 0.6178 0.9104
1.500 0.3051 0.00668 0.00214 -0.0076 0.5931 0.9738
1.750 0.3536 0.00689 0.00218 -0.0117 0.5556 0.9890
2.000 0.3987 0.00752 0.00223 -0.0157 0.4187 0.9967
2.250 0.4366 0.00856 0.00259 -0.0187 0.2803 1.0000
2.500 0.4625 0.00889 0.00273 -0.0184 0.2502 1.0000
2.750 0.4881 0.00913 0.00286 -0.0181 0.2325 1.0000
3.000 0.5136 0.00938 0.00299 -0.0177 0.2194 1.0000
3.250 0.5391 0.00955 0.00312 -0.0172 0.2102 1.0000
3.500 0.5643 0.00978 0.00329 -0.0168 0.2021 1.0000
3.750 0.5896 0.00995 0.00342 -0.0163 0.1955 1.0000
4.000 0.6142 0.01024 0.00363 -0.0157 0.1882 1.0000
4.250 0.6395 0.01038 0.00378 -0.0152 0.1833 1.0000
4.500 0.6644 0.01059 0.00395 -0.0146 0.1781 1.0000
4.750 0.6884 0.01094 0.00423 -0.0140 0.1723 1.0000
5.000 0.7136 0.01109 0.00440 -0.0134 0.1689 1.0000
5.250 0.7385 0.01127 0.00458 -0.0129 0.1646 1.0000
5.500 0.7627 0.01155 0.00481 -0.0122 0.1600 1.0000
5.750 0.7866 0.01189 0.00514 -0.0115 0.1560 1.0000
6.000 0.8115 0.01207 0.00535 -0.0110 0.1529 1.0000
6.250 0.8361 0.01229 0.00557 -0.0104 0.1492 1.0000
6.750 0.8831 0.01301 0.00624 -0.0090 0.1416 1.0000
7.000 0.9078 0.01321 0.00648 -0.0084 0.1390 1.0000
7.250 0.9321 0.01344 0.00674 -0.0078 0.1359 1.0000
7.500 0.9561 0.01372 0.00701 -0.0072 0.1325 1.0000
7.750 0.9780 0.01425 0.00749 -0.0063 0.1285 1.0000
8.000 1.0021 0.01450 0.00780 -0.0057 0.1264 1.0000
8.250 1.0263 0.01475 0.00811 -0.0051 0.1237 1.0000
8.500 1.0503 0.01502 0.00839 -0.0045 0.1207 1.0000
8.750 1.0734 0.01538 0.00874 -0.0039 0.1176 1.0000
9.000 1.0947 0.01600 0.00935 -0.0030 0.1143 1.0000
9.250 1.1190 0.01622 0.00966 -0.0025 0.1121 1.0000
9.500 1.1428 0.01650 0.00999 -0.0020 0.1093 1.0000
9.750 1.1660 0.01682 0.01033 -0.0014 0.1065 1.0000
10.000 1.1874 0.01736 0.01084 -0.0007 0.1033 1.0000
10.250 1.2093 0.01786 0.01140 0.0000 0.1008 1.0000
10.500 1.2325 0.01815 0.01178 0.0005 0.0983 1.0000
10.750 1.2551 0.01850 0.01218 0.0011 0.0955 1.0000
11.000 1.2764 0.01895 0.01263 0.0018 0.0927 1.0000
11.250 1.2950 0.01970 0.01339 0.0028 0.0895 1.0000
11.500 1.3173 0.02001 0.01381 0.0033 0.0874 1.0000
11.750 1.3386 0.02039 0.01426 0.0040 0.0846 1.0000
12.000 1.3583 0.02087 0.01475 0.0047 0.0817 1.0000
12.250 1.3744 0.02165 0.01554 0.0058 0.0783 1.0000
12.500 1.3953 0.02196 0.01596 0.0065 0.0756 1.0000
12.750 1.4126 0.02244 0.01647 0.0075 0.0725 1.0000
13.000 1.4249 0.02327 0.01731 0.0089 0.0694 1.0000
13.250 1.4395 0.02404 0.01817 0.0100 0.0671 1.0000
13.500 1.4556 0.02473 0.01895 0.0107 0.0644 1.0000
13.750 1.4691 0.02566 0.01991 0.0115 0.0617 1.0000
14.000 1.4777 0.02703 0.02130 0.0124 0.0589 1.0000
14.250 1.4933 0.02788 0.02228 0.0130 0.0565 1.0000
14.500 1.5055 0.02902 0.02348 0.0135 0.0538 1.0000
14.750 1.5125 0.03065 0.02513 0.0141 0.0511 1.0000
15.000 1.5233 0.03198 0.02657 0.0146 0.0488 1.0000
15.250 1.5323 0.03349 0.02816 0.0150 0.0463 1.0000
15.500 1.5363 0.03551 0.03022 0.0154 0.0439 1.0000
15.750 1.5410 0.03750 0.03231 0.0157 0.0418 1.0000
16.000 1.5457 0.03955 0.03446 0.0159 0.0395 1.0000
16.250 1.5449 0.04220 0.03717 0.0159 0.0375 1.0000
16.500 1.5418 0.04519 0.04026 0.0157 0.0357 1.0000
16.750 1.5409 0.04803 0.04322 0.0154 0.0338 1.0000
17.000 1.5340 0.05167 0.04696 0.0147 0.0322 1.0000
17.250 1.5204 0.05631 0.05169 0.0135 0.0310 1.0000
17.500 1.5081 0.06108 0.05661 0.0119 0.0299 1.0000
17.750 1.4951 0.06630 0.06199 0.0099 0.0288 1.0000
18.000 1.4752 0.07288 0.06872 0.0069 0.0281 1.0000
18.250 1.4489 0.08103 0.07705 0.0029 0.0278 1.0000
18.500 1.4158 0.09079 0.08700 -0.0021 0.0279 1.0000
18.750 1.3788 0.10139 0.09779 -0.0075 0.0282 1.0000
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