NACA 1410 (naca1410-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 500,000 Max Cl/Cd: 63.58 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1410-il-500000-n5.txt Download as CSV file: xf-naca1410-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1410
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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.9296 0.11457 0.11192 0.0039 1.0000 0.0095
-15.500 -0.9918 0.09804 0.09522 -0.0049 1.0000 0.0092
-15.250 -1.0532 0.08228 0.07933 -0.0137 1.0000 0.0089
-15.000 -1.1114 0.06642 0.06325 -0.0238 1.0000 0.0086
-14.750 -1.1479 0.05435 0.05094 -0.0331 1.0000 0.0085
-14.500 -1.1675 0.04645 0.04281 -0.0398 1.0000 0.0085
-14.250 -1.1791 0.04119 0.03735 -0.0436 1.0000 0.0085
-14.000 -1.1859 0.03757 0.03355 -0.0450 1.0000 0.0086
-13.750 -1.1892 0.03495 0.03074 -0.0447 1.0000 0.0088
-13.500 -1.1897 0.03292 0.02855 -0.0434 1.0000 0.0090
-13.250 -1.1869 0.03128 0.02675 -0.0415 1.0000 0.0092
-13.000 -1.1782 0.02980 0.02509 -0.0401 1.0000 0.0093
-12.750 -1.1701 0.02812 0.02327 -0.0387 1.0000 0.0097
-12.500 -1.1571 0.02679 0.02184 -0.0376 1.0000 0.0100
-12.250 -1.1416 0.02567 0.02061 -0.0366 1.0000 0.0104
-12.000 -1.1246 0.02464 0.01946 -0.0356 1.0000 0.0108
-11.750 -1.1068 0.02366 0.01836 -0.0347 1.0000 0.0112
-11.500 -1.0883 0.02273 0.01728 -0.0337 1.0000 0.0117
-11.250 -1.0690 0.02184 0.01627 -0.0328 1.0000 0.0121
-11.000 -1.0496 0.02096 0.01528 -0.0319 1.0000 0.0127
-10.750 -1.0292 0.02018 0.01444 -0.0311 1.0000 0.0134
-10.500 -1.0076 0.01958 0.01378 -0.0304 1.0000 0.0143
-10.250 -0.9857 0.01900 0.01313 -0.0296 1.0000 0.0152
-10.000 -0.9640 0.01841 0.01243 -0.0288 1.0000 0.0161
-9.750 -0.9426 0.01779 0.01175 -0.0279 1.0000 0.0170
-9.500 -0.9202 0.01734 0.01128 -0.0272 1.0000 0.0181
-9.250 -0.8977 0.01692 0.01081 -0.0263 1.0000 0.0192
-9.000 -0.8754 0.01652 0.01034 -0.0255 1.0000 0.0205
-8.750 -0.8529 0.01614 0.00989 -0.0245 1.0000 0.0215
-8.500 -0.8315 0.01564 0.00936 -0.0236 1.0000 0.0229
-8.250 -0.8090 0.01529 0.00899 -0.0226 1.0000 0.0241
-8.000 -0.7867 0.01495 0.00860 -0.0217 1.0000 0.0254
-7.750 -0.7643 0.01464 0.00823 -0.0207 1.0000 0.0267
-7.500 -0.7417 0.01438 0.00790 -0.0198 1.0000 0.0275
-7.250 -0.7210 0.01381 0.00730 -0.0186 1.0000 0.0290
-7.000 -0.6984 0.01342 0.00690 -0.0177 0.9998 0.0304
-6.750 -0.6658 0.01307 0.00651 -0.0189 0.9977 0.0320
-6.500 -0.6327 0.01272 0.00612 -0.0202 0.9955 0.0335
-6.250 -0.5996 0.01242 0.00575 -0.0215 0.9931 0.0348
-6.000 -0.5676 0.01200 0.00530 -0.0226 0.9900 0.0363
-5.750 -0.5346 0.01160 0.00489 -0.0238 0.9871 0.0386
-5.500 -0.5002 0.01126 0.00454 -0.0254 0.9848 0.0405
-5.250 -0.4686 0.01098 0.00422 -0.0262 0.9804 0.0425
-5.000 -0.4359 0.01071 0.00393 -0.0273 0.9764 0.0446
-4.750 -0.4035 0.01039 0.00363 -0.0284 0.9723 0.0495
-4.500 -0.3734 0.01013 0.00337 -0.0289 0.9658 0.0552
-4.250 -0.3411 0.00983 0.00313 -0.0299 0.9607 0.0675
-4.000 -0.3125 0.00956 0.00291 -0.0300 0.9524 0.0825
-3.750 -0.2822 0.00929 0.00270 -0.0305 0.9450 0.0996
-3.500 -0.2538 0.00903 0.00252 -0.0307 0.9354 0.1201
-3.250 -0.2257 0.00877 0.00235 -0.0307 0.9253 0.1458
-3.000 -0.1978 0.00852 0.00218 -0.0306 0.9143 0.1723
-2.750 -0.1705 0.00832 0.00204 -0.0305 0.9017 0.1984
-2.500 -0.1436 0.00809 0.00191 -0.0302 0.8879 0.2319
-2.250 -0.1168 0.00789 0.00180 -0.0299 0.8732 0.2695
-2.000 -0.0901 0.00772 0.00168 -0.0296 0.8573 0.3007
-1.750 -0.0638 0.00749 0.00155 -0.0292 0.8407 0.3393
-1.500 -0.0387 0.00711 0.00149 -0.0287 0.8229 0.4406
-1.250 -0.0120 0.00701 0.00145 -0.0283 0.8040 0.4848
-1.000 0.0148 0.00695 0.00139 -0.0280 0.7838 0.5109
-0.750 0.0412 0.00687 0.00134 -0.0276 0.7622 0.5429
-0.500 0.0676 0.00681 0.00131 -0.0271 0.7383 0.5744
-0.250 0.0938 0.00675 0.00129 -0.0267 0.7146 0.6090
0.000 0.1198 0.00668 0.00129 -0.0262 0.6915 0.6541
0.250 0.1456 0.00661 0.00131 -0.0256 0.6690 0.7008
0.750 0.1963 0.00652 0.00138 -0.0241 0.6235 0.7950
1.000 0.2212 0.00652 0.00145 -0.0233 0.5989 0.8381
1.250 0.2463 0.00658 0.00152 -0.0224 0.5730 0.8757
1.500 0.2725 0.00668 0.00160 -0.0217 0.5483 0.9072
1.750 0.3008 0.00681 0.00168 -0.0216 0.5250 0.9303
2.000 0.3312 0.00697 0.00176 -0.0220 0.4984 0.9480
2.250 0.3624 0.00724 0.00185 -0.0228 0.4554 0.9624
2.500 0.3939 0.00751 0.00195 -0.0236 0.4148 0.9735
2.750 0.4271 0.00776 0.00206 -0.0249 0.3776 0.9813
3.000 0.4602 0.00808 0.00220 -0.0262 0.3330 0.9885
3.250 0.4936 0.00841 0.00235 -0.0276 0.2913 0.9945
3.500 0.5270 0.00880 0.00252 -0.0290 0.2450 0.9985
3.750 0.5540 0.00913 0.00271 -0.0291 0.2094 1.0000
4.000 0.5774 0.00946 0.00289 -0.0283 0.1783 1.0000
4.250 0.6008 0.00980 0.00311 -0.0275 0.1490 1.0000
4.500 0.6240 0.01017 0.00335 -0.0267 0.1205 1.0000
4.750 0.6474 0.01054 0.00359 -0.0259 0.0967 1.0000
5.000 0.6713 0.01089 0.00385 -0.0252 0.0788 1.0000
5.250 0.6952 0.01125 0.00414 -0.0246 0.0632 1.0000
5.500 0.7193 0.01160 0.00444 -0.0239 0.0520 1.0000
5.750 0.7440 0.01192 0.00474 -0.0233 0.0464 1.0000
6.000 0.7685 0.01226 0.00506 -0.0228 0.0427 1.0000
6.250 0.7930 0.01262 0.00544 -0.0222 0.0397 1.0000
6.500 0.8180 0.01293 0.00578 -0.0217 0.0382 1.0000
6.750 0.8427 0.01327 0.00616 -0.0211 0.0369 1.0000
7.000 0.8672 0.01364 0.00655 -0.0206 0.0354 1.0000
7.250 0.8913 0.01405 0.00699 -0.0200 0.0337 1.0000
7.500 0.9144 0.01460 0.00757 -0.0193 0.0319 1.0000
7.750 0.9385 0.01501 0.00802 -0.0188 0.0309 1.0000
8.000 0.9628 0.01538 0.00845 -0.0182 0.0299 1.0000
8.250 0.9867 0.01579 0.00891 -0.0177 0.0287 1.0000
8.500 1.0105 0.01621 0.00938 -0.0171 0.0274 1.0000
8.750 1.0336 0.01670 0.00989 -0.0165 0.0261 1.0000
9.000 1.0546 0.01741 0.01063 -0.0156 0.0246 1.0000
9.250 1.0782 0.01781 0.01111 -0.0150 0.0238 1.0000
9.500 1.1013 0.01825 0.01162 -0.0144 0.0227 1.0000
9.750 1.1242 0.01870 0.01214 -0.0138 0.0215 1.0000
10.000 1.1469 0.01915 0.01263 -0.0132 0.0202 1.0000
10.250 1.1682 0.01972 0.01321 -0.0124 0.0190 1.0000
10.500 1.1895 0.02028 0.01385 -0.0116 0.0180 1.0000
10.750 1.2104 0.02085 0.01450 -0.0107 0.0169 1.0000
11.000 1.2311 0.02142 0.01513 -0.0099 0.0159 1.0000
11.250 1.2511 0.02202 0.01577 -0.0090 0.0149 1.0000
11.500 1.2690 0.02279 0.01659 -0.0079 0.0140 1.0000
11.750 1.2866 0.02354 0.01745 -0.0067 0.0133 1.0000
12.000 1.3034 0.02431 0.01831 -0.0054 0.0125 1.0000
12.250 1.3190 0.02513 0.01919 -0.0041 0.0118 1.0000
12.500 1.3313 0.02601 0.02014 -0.0022 0.0113 1.0000
12.750 1.3399 0.02714 0.02136 0.0000 0.0107 1.0000
13.000 1.3482 0.02831 0.02265 0.0020 0.0104 1.0000
13.250 1.3558 0.02957 0.02404 0.0038 0.0101 1.0000
13.500 1.3621 0.03100 0.02560 0.0055 0.0098 1.0000
13.750 1.3672 0.03261 0.02733 0.0069 0.0095 1.0000
14.000 1.3710 0.03442 0.02928 0.0081 0.0093 1.0000
14.250 1.3738 0.03647 0.03145 0.0089 0.0090 1.0000
14.500 1.3751 0.03883 0.03394 0.0093 0.0088 1.0000
14.750 1.3745 0.04157 0.03680 0.0093 0.0086 1.0000
15.000 1.3717 0.04480 0.04016 0.0087 0.0084 1.0000
15.250 1.3659 0.04865 0.04416 0.0076 0.0082 1.0000
15.500 1.3569 0.05326 0.04891 0.0057 0.0081 1.0000
15.750 1.3442 0.05866 0.05447 0.0032 0.0080 1.0000
16.000 1.3285 0.06485 0.06082 0.0000 0.0079 1.0000
16.250 1.3096 0.07176 0.06789 -0.0036 0.0079 1.0000
16.500 1.2886 0.07928 0.07557 -0.0076 0.0079 1.0000
16.750 1.2644 0.08759 0.08406 -0.0119 0.0079 1.0000
17.000 1.2392 0.09638 0.09301 -0.0166 0.0079 1.0000
17.250 1.2117 0.10584 0.10263 -0.0215 0.0080 1.0000
17.500 1.1821 0.11600 0.11295 -0.0268 0.0081 1.0000
17.750 1.1500 0.12701 0.12412 -0.0325 0.0082 1.0000
18.000 1.1158 0.13892 0.13620 -0.0389 0.0083 1.0000
18.250 1.0736 0.15354 0.15099 -0.0468 0.0085 1.0000
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