NACA 1410 (naca1410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.88 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1410-il-1000000.txt Download as CSV file: xf-naca1410-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9565 0.12163 0.11966 0.0079 1.0000 0.0090
-16.250 -1.0222 0.10434 0.10221 -0.0013 1.0000 0.0088
-16.000 -1.0870 0.08827 0.08600 -0.0102 1.0000 0.0085
-15.750 -1.1528 0.07198 0.06950 -0.0197 1.0000 0.0082
-15.500 -1.2031 0.05747 0.05473 -0.0298 1.0000 0.0081
-15.250 -1.2301 0.04798 0.04502 -0.0374 1.0000 0.0080
-15.000 -1.2442 0.04164 0.03848 -0.0426 1.0000 0.0081
-14.750 -1.2521 0.03738 0.03407 -0.0451 1.0000 0.0081
-14.500 -1.2567 0.03434 0.03087 -0.0457 1.0000 0.0082
-14.250 -1.2584 0.03207 0.02847 -0.0450 1.0000 0.0084
-14.000 -1.2578 0.03028 0.02655 -0.0433 1.0000 0.0085
-13.750 -1.2536 0.02882 0.02497 -0.0413 1.0000 0.0086
-13.500 -1.2436 0.02745 0.02347 -0.0400 1.0000 0.0088
-13.250 -1.2307 0.02623 0.02211 -0.0388 1.0000 0.0090
-13.000 -1.2155 0.02516 0.02092 -0.0377 1.0000 0.0092
-12.750 -1.1982 0.02424 0.01989 -0.0368 1.0000 0.0093
-12.500 -1.1894 0.02229 0.01774 -0.0350 1.0000 0.0098
-12.250 -1.1735 0.02107 0.01642 -0.0339 1.0000 0.0102
-12.000 -1.1540 0.02023 0.01551 -0.0331 1.0000 0.0106
-11.750 -1.1333 0.01952 0.01472 -0.0323 1.0000 0.0110
-11.500 -1.1120 0.01885 0.01398 -0.0316 1.0000 0.0115
-11.250 -1.0902 0.01825 0.01330 -0.0308 1.0000 0.0120
-11.000 -1.0676 0.01775 0.01273 -0.0302 1.0000 0.0124
-10.750 -1.0491 0.01669 0.01156 -0.0290 1.0000 0.0133
-10.500 -1.0273 0.01612 0.01096 -0.0282 1.0000 0.0142
-10.250 -1.0045 0.01569 0.01050 -0.0274 1.0000 0.0149
-10.000 -0.9818 0.01529 0.01006 -0.0266 1.0000 0.0158
-9.750 -0.9588 0.01496 0.00967 -0.0258 1.0000 0.0163
-9.500 -0.9387 0.01425 0.00893 -0.0246 1.0000 0.0180
-9.250 -0.9154 0.01401 0.00870 -0.0238 1.0000 0.0192
-9.000 -0.8919 0.01382 0.00849 -0.0230 1.0000 0.0205
-8.750 -0.8681 0.01372 0.00836 -0.0222 1.0000 0.0213
-8.500 -0.8482 0.01306 0.00767 -0.0209 1.0000 0.0231
-8.250 -0.8256 0.01284 0.00746 -0.0199 1.0000 0.0244
-8.000 -0.8030 0.01264 0.00725 -0.0189 1.0000 0.0257
-7.750 -0.7802 0.01249 0.00707 -0.0180 1.0000 0.0268
-7.500 -0.7571 0.01244 0.00700 -0.0170 1.0000 0.0275
-7.250 -0.7376 0.01172 0.00621 -0.0156 1.0000 0.0295
-7.000 -0.7124 0.01138 0.00587 -0.0153 0.9997 0.0310
-6.750 -0.6783 0.01111 0.00559 -0.0168 0.9983 0.0325
-6.500 -0.6437 0.01087 0.00533 -0.0183 0.9968 0.0339
-6.250 -0.6087 0.01064 0.00507 -0.0200 0.9953 0.0349
-6.000 -0.5740 0.01023 0.00461 -0.0216 0.9941 0.0363
-5.750 -0.5418 0.00979 0.00415 -0.0226 0.9916 0.0387
-5.500 -0.5078 0.00949 0.00385 -0.0240 0.9893 0.0407
-5.250 -0.4729 0.00924 0.00358 -0.0256 0.9874 0.0426
-5.000 -0.4372 0.00901 0.00333 -0.0274 0.9859 0.0440
-4.750 -0.4012 0.00870 0.00301 -0.0291 0.9846 0.0473
-4.500 -0.3705 0.00842 0.00276 -0.0298 0.9801 0.0529
-4.250 -0.3380 0.00810 0.00252 -0.0308 0.9763 0.0683
-4.000 -0.3069 0.00775 0.00231 -0.0315 0.9721 0.0954
-3.750 -0.2790 0.00747 0.00213 -0.0315 0.9649 0.1204
-3.500 -0.2505 0.00720 0.00197 -0.0316 0.9582 0.1479
-3.250 -0.2235 0.00696 0.00182 -0.0314 0.9495 0.1764
-3.000 -0.1968 0.00673 0.00170 -0.0311 0.9399 0.2068
-2.750 -0.1701 0.00652 0.00158 -0.0307 0.9300 0.2400
-2.500 -0.1437 0.00632 0.00148 -0.0303 0.9181 0.2754
-2.250 -0.1170 0.00615 0.00138 -0.0300 0.9054 0.3061
-2.000 -0.0907 0.00591 0.00126 -0.0296 0.8916 0.3497
-1.750 -0.0653 0.00553 0.00119 -0.0291 0.8765 0.4488
-1.500 -0.0385 0.00543 0.00114 -0.0287 0.8598 0.4887
-1.000 0.0157 0.00533 0.00104 -0.0281 0.8217 0.5346
-0.750 0.0425 0.00524 0.00100 -0.0278 0.8017 0.5679
-0.500 0.0691 0.00515 0.00098 -0.0274 0.7811 0.6089
-0.250 0.0954 0.00502 0.00097 -0.0270 0.7599 0.6664
0.000 0.1213 0.00491 0.00097 -0.0265 0.7374 0.7238
0.250 0.1473 0.00485 0.00099 -0.0259 0.7139 0.7706
0.500 0.1728 0.00482 0.00102 -0.0252 0.6876 0.8154
0.750 0.1984 0.00482 0.00106 -0.0245 0.6609 0.8550
1.000 0.2235 0.00485 0.00111 -0.0236 0.6365 0.8925
1.250 0.2487 0.00492 0.00118 -0.0228 0.6119 0.9236
1.500 0.2746 0.00507 0.00124 -0.0221 0.5785 0.9473
1.750 0.3033 0.00528 0.00131 -0.0221 0.5376 0.9642
2.000 0.3351 0.00545 0.00138 -0.0229 0.5097 0.9760
2.250 0.3672 0.00562 0.00145 -0.0238 0.4839 0.9845
2.500 0.4029 0.00584 0.00153 -0.0256 0.4467 0.9881
2.750 0.4386 0.00604 0.00162 -0.0273 0.4175 0.9921
3.000 0.4743 0.00629 0.00172 -0.0292 0.3812 0.9954
3.250 0.5098 0.00657 0.00183 -0.0310 0.3387 0.9979
3.500 0.5435 0.00689 0.00197 -0.0325 0.2947 1.0000
3.750 0.5668 0.00719 0.00211 -0.0317 0.2545 1.0000
4.000 0.5900 0.00752 0.00226 -0.0308 0.2165 1.0000
4.250 0.6132 0.00786 0.00244 -0.0300 0.1802 1.0000
4.500 0.6362 0.00822 0.00264 -0.0291 0.1458 1.0000
4.750 0.6592 0.00861 0.00287 -0.0283 0.1138 1.0000
5.000 0.6823 0.00900 0.00312 -0.0274 0.0844 1.0000
5.250 0.7051 0.00944 0.00341 -0.0265 0.0578 1.0000
5.500 0.7291 0.00978 0.00369 -0.0257 0.0479 1.0000
5.750 0.7536 0.01008 0.00396 -0.0251 0.0438 1.0000
6.000 0.7779 0.01044 0.00432 -0.0244 0.0404 1.0000
6.250 0.8032 0.01070 0.00461 -0.0239 0.0395 1.0000
6.500 0.8286 0.01095 0.00489 -0.0234 0.0383 1.0000
6.750 0.8538 0.01123 0.00519 -0.0230 0.0370 1.0000
7.000 0.8789 0.01154 0.00552 -0.0225 0.0354 1.0000
7.250 0.9034 0.01194 0.00593 -0.0219 0.0337 1.0000
7.500 0.9259 0.01260 0.00665 -0.0211 0.0316 1.0000
7.750 0.9512 0.01288 0.00697 -0.0207 0.0311 1.0000
8.000 0.9767 0.01313 0.00725 -0.0203 0.0302 1.0000
8.250 1.0017 0.01344 0.00759 -0.0199 0.0292 1.0000
8.500 1.0265 0.01377 0.00794 -0.0195 0.0280 1.0000
8.750 1.0510 0.01414 0.00831 -0.0190 0.0266 1.0000
9.000 1.0705 0.01510 0.00934 -0.0179 0.0244 1.0000
9.250 1.0967 0.01522 0.00947 -0.0177 0.0239 1.0000
9.500 1.1221 0.01544 0.00973 -0.0174 0.0229 1.0000
9.750 1.1471 0.01570 0.01001 -0.0170 0.0217 1.0000
10.000 1.1717 0.01599 0.01029 -0.0166 0.0203 1.0000
10.250 1.1925 0.01670 0.01103 -0.0157 0.0186 1.0000
10.500 1.2175 0.01691 0.01127 -0.0154 0.0178 1.0000
10.750 1.2415 0.01723 0.01161 -0.0149 0.0166 1.0000
11.000 1.2645 0.01764 0.01202 -0.0144 0.0154 1.0000
11.250 1.2831 0.01848 0.01291 -0.0132 0.0141 1.0000
11.500 1.3049 0.01896 0.01345 -0.0124 0.0135 1.0000
11.750 1.3257 0.01951 0.01405 -0.0116 0.0128 1.0000
12.000 1.3458 0.02011 0.01468 -0.0107 0.0121 1.0000
12.250 1.3633 0.02091 0.01552 -0.0094 0.0113 1.0000
12.500 1.3754 0.02212 0.01685 -0.0075 0.0106 1.0000
12.750 1.3930 0.02279 0.01759 -0.0063 0.0103 1.0000
13.000 1.4080 0.02357 0.01846 -0.0048 0.0099 1.0000
13.250 1.4195 0.02442 0.01939 -0.0028 0.0096 1.0000
13.500 1.4296 0.02536 0.02041 -0.0007 0.0093 1.0000
13.750 1.4386 0.02641 0.02154 0.0013 0.0090 1.0000
14.000 1.4455 0.02765 0.02286 0.0033 0.0088 1.0000
14.250 1.4491 0.02921 0.02452 0.0052 0.0085 1.0000
14.500 1.4477 0.03132 0.02674 0.0070 0.0082 1.0000
14.750 1.4397 0.03424 0.02984 0.0084 0.0080 1.0000
15.000 1.4338 0.03729 0.03304 0.0090 0.0079 1.0000
15.250 1.4348 0.03985 0.03572 0.0090 0.0078 1.0000
15.500 1.4336 0.04288 0.03889 0.0085 0.0077 1.0000
15.750 1.4300 0.04644 0.04258 0.0075 0.0076 1.0000
16.000 1.4231 0.05066 0.04695 0.0060 0.0076 1.0000
16.250 1.4136 0.05553 0.05195 0.0038 0.0075 1.0000
16.500 1.4001 0.06119 0.05777 0.0011 0.0074 1.0000
16.750 1.3830 0.06768 0.06440 -0.0022 0.0074 1.0000
17.000 1.3614 0.07502 0.07190 -0.0059 0.0074 1.0000
17.250 1.3368 0.08318 0.08021 -0.0101 0.0074 1.0000
17.500 1.3084 0.09219 0.08937 -0.0148 0.0074 1.0000
17.750 1.2770 0.10207 0.09940 -0.0199 0.0075 1.0000
18.000 1.2447 0.11230 0.10978 -0.0251 0.0076 1.0000
18.250 1.2131 0.12281 0.12041 -0.0306 0.0076 1.0000
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