NACA 1410 (naca1410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1410 (naca1410-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.32 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1410-il-1000000-n5.txt Download as CSV file: xf-naca1410-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0860 0.10096 0.09860 -0.0040 1.0000 0.0061
-16.500 -1.2328 0.06971 0.06695 -0.0220 1.0000 0.0056
-16.250 -1.2897 0.05406 0.05100 -0.0333 1.0000 0.0055
-16.000 -1.3138 0.04558 0.04230 -0.0401 1.0000 0.0054
-15.750 -1.3270 0.04003 0.03657 -0.0441 1.0000 0.0055
-15.500 -1.3346 0.03621 0.03259 -0.0459 1.0000 0.0055
-15.250 -1.3383 0.03344 0.02969 -0.0460 1.0000 0.0056
-15.000 -1.3390 0.03135 0.02747 -0.0451 1.0000 0.0057
-14.750 -1.3371 0.02970 0.02571 -0.0434 1.0000 0.0058
-14.500 -1.3325 0.02833 0.02423 -0.0414 1.0000 0.0059
-14.250 -1.3221 0.02708 0.02287 -0.0400 1.0000 0.0060
-14.000 -1.3092 0.02593 0.02161 -0.0388 1.0000 0.0062
-13.750 -1.2944 0.02487 0.02045 -0.0377 1.0000 0.0063
-13.500 -1.2783 0.02388 0.01936 -0.0367 1.0000 0.0065
-13.250 -1.2608 0.02296 0.01834 -0.0358 1.0000 0.0067
-13.000 -1.2424 0.02212 0.01739 -0.0349 1.0000 0.0068
-12.750 -1.2229 0.02134 0.01652 -0.0341 1.0000 0.0069
-12.500 -1.2044 0.02039 0.01548 -0.0332 1.0000 0.0073
-12.250 -1.1846 0.01957 0.01459 -0.0324 1.0000 0.0076
-12.000 -1.1638 0.01886 0.01381 -0.0316 1.0000 0.0079
-11.750 -1.1424 0.01820 0.01309 -0.0309 1.0000 0.0083
-11.500 -1.1205 0.01760 0.01243 -0.0302 1.0000 0.0087
-11.250 -1.0983 0.01705 0.01180 -0.0295 1.0000 0.0091
-11.000 -1.0757 0.01654 0.01121 -0.0289 1.0000 0.0093
-10.750 -1.0540 0.01591 0.01054 -0.0280 1.0000 0.0100
-10.500 -1.0318 0.01538 0.00997 -0.0273 1.0000 0.0107
-10.250 -1.0094 0.01491 0.00946 -0.0264 1.0000 0.0113
-10.000 -0.9870 0.01447 0.00898 -0.0256 1.0000 0.0120
-9.750 -0.9646 0.01407 0.00851 -0.0247 1.0000 0.0126
-9.500 -0.9424 0.01364 0.00808 -0.0238 1.0000 0.0137
-9.250 -0.9199 0.01328 0.00770 -0.0229 1.0000 0.0150
-9.000 -0.8974 0.01295 0.00734 -0.0219 1.0000 0.0161
-8.750 -0.8751 0.01261 0.00701 -0.0210 1.0000 0.0175
-8.500 -0.8494 0.01232 0.00671 -0.0207 0.9995 0.0190
-8.250 -0.8182 0.01203 0.00640 -0.0216 0.9981 0.0204
-8.000 -0.7866 0.01178 0.00611 -0.0225 0.9966 0.0213
-7.750 -0.7549 0.01143 0.00576 -0.0236 0.9951 0.0229
-7.500 -0.7231 0.01115 0.00548 -0.0246 0.9934 0.0243
-7.250 -0.6922 0.01089 0.00520 -0.0254 0.9910 0.0255
-7.000 -0.6602 0.01066 0.00494 -0.0264 0.9886 0.0266
-6.750 -0.6277 0.01045 0.00471 -0.0274 0.9863 0.0273
-6.500 -0.5961 0.01019 0.00442 -0.0283 0.9834 0.0281
-6.250 -0.5669 0.00986 0.00408 -0.0287 0.9784 0.0298
-6.000 -0.5356 0.00960 0.00381 -0.0295 0.9744 0.0313
-5.750 -0.5067 0.00937 0.00358 -0.0298 0.9683 0.0326
-5.500 -0.4768 0.00917 0.00335 -0.0302 0.9622 0.0339
-5.250 -0.4487 0.00898 0.00314 -0.0302 0.9543 0.0346
-5.000 -0.4203 0.00881 0.00294 -0.0302 0.9459 0.0353
-4.750 -0.3932 0.00860 0.00271 -0.0300 0.9354 0.0381
-4.500 -0.3661 0.00842 0.00252 -0.0297 0.9244 0.0408
-4.250 -0.3390 0.00827 0.00235 -0.0294 0.9125 0.0438
-4.000 -0.3123 0.00809 0.00217 -0.0291 0.8994 0.0514
-3.750 -0.2856 0.00791 0.00201 -0.0288 0.8853 0.0642
-3.500 -0.2587 0.00775 0.00186 -0.0285 0.8705 0.0778
-3.250 -0.2317 0.00762 0.00172 -0.0283 0.8547 0.0910
-3.000 -0.2046 0.00749 0.00160 -0.0281 0.8382 0.1059
-2.750 -0.1775 0.00736 0.00148 -0.0279 0.8211 0.1240
-2.500 -0.1505 0.00722 0.00137 -0.0276 0.8027 0.1495
-2.250 -0.1235 0.00709 0.00128 -0.0275 0.7844 0.1757
-2.000 -0.0965 0.00697 0.00119 -0.0273 0.7648 0.2056
-1.750 -0.0694 0.00685 0.00112 -0.0271 0.7444 0.2386
-1.500 -0.0422 0.00677 0.00107 -0.0269 0.7217 0.2691
-1.250 -0.0149 0.00675 0.00102 -0.0268 0.6971 0.2886
-0.750 0.0388 0.00649 0.00091 -0.0265 0.6505 0.3769
-0.500 0.0654 0.00630 0.00091 -0.0263 0.6286 0.4589
-0.250 0.0928 0.00628 0.00091 -0.0262 0.6077 0.4926
0.000 0.1204 0.00627 0.00091 -0.0261 0.5863 0.5180
0.250 0.1479 0.00630 0.00092 -0.0260 0.5641 0.5371
0.500 0.1753 0.00633 0.00093 -0.0259 0.5388 0.5590
0.750 0.2026 0.00634 0.00096 -0.0258 0.5147 0.5860
1.000 0.2296 0.00630 0.00099 -0.0256 0.4932 0.6309
1.250 0.2563 0.00626 0.00104 -0.0253 0.4716 0.6815
1.500 0.2824 0.00631 0.00110 -0.0250 0.4337 0.7278
1.750 0.3079 0.00642 0.00118 -0.0245 0.3883 0.7732
2.000 0.3337 0.00646 0.00127 -0.0240 0.3610 0.8159
2.500 0.3847 0.00673 0.00149 -0.0229 0.2945 0.8807
2.750 0.4098 0.00690 0.00161 -0.0222 0.2629 0.9086
3.000 0.4356 0.00708 0.00175 -0.0217 0.2362 0.9351
3.250 0.4628 0.00738 0.00191 -0.0216 0.1970 0.9537
3.500 0.4922 0.00767 0.00207 -0.0220 0.1650 0.9665
3.750 0.5228 0.00798 0.00225 -0.0227 0.1353 0.9767
4.000 0.5539 0.00830 0.00244 -0.0235 0.1070 0.9852
4.250 0.5863 0.00860 0.00263 -0.0247 0.0865 0.9909
4.500 0.6176 0.00887 0.00283 -0.0255 0.0708 0.9952
4.750 0.6497 0.00919 0.00306 -0.0266 0.0535 0.9982
5.000 0.6785 0.00947 0.00327 -0.0270 0.0436 1.0000
5.250 0.7030 0.00970 0.00348 -0.0263 0.0389 1.0000
5.500 0.7278 0.00991 0.00369 -0.0257 0.0366 1.0000
5.750 0.7527 0.01015 0.00391 -0.0251 0.0346 1.0000
6.000 0.7777 0.01041 0.00417 -0.0246 0.0323 1.0000
6.250 0.8030 0.01066 0.00444 -0.0241 0.0313 1.0000
6.500 0.8285 0.01089 0.00468 -0.0236 0.0308 1.0000
6.750 0.8541 0.01112 0.00493 -0.0232 0.0299 1.0000
7.000 0.8796 0.01138 0.00520 -0.0228 0.0289 1.0000
7.250 0.9050 0.01165 0.00549 -0.0224 0.0277 1.0000
7.500 0.9301 0.01196 0.00581 -0.0220 0.0265 1.0000
7.750 0.9548 0.01233 0.00619 -0.0215 0.0251 1.0000
8.000 0.9798 0.01266 0.00654 -0.0211 0.0242 1.0000
8.250 1.0053 0.01291 0.00683 -0.0208 0.0237 1.0000
8.500 1.0306 0.01319 0.00714 -0.0204 0.0229 1.0000
8.750 1.0557 0.01348 0.00746 -0.0200 0.0219 1.0000
9.000 1.0805 0.01380 0.00777 -0.0196 0.0206 1.0000
9.250 1.1049 0.01417 0.00814 -0.0192 0.0193 1.0000
9.500 1.1291 0.01454 0.00856 -0.0187 0.0184 1.0000
9.750 1.1535 0.01488 0.00893 -0.0182 0.0174 1.0000
10.000 1.1775 0.01524 0.00931 -0.0178 0.0161 1.0000
10.250 1.2009 0.01566 0.00971 -0.0172 0.0145 1.0000
10.500 1.2240 0.01610 0.01019 -0.0166 0.0134 1.0000
10.750 1.2467 0.01657 0.01068 -0.0160 0.0123 1.0000
11.000 1.2688 0.01709 0.01123 -0.0153 0.0113 1.0000
11.250 1.2903 0.01764 0.01182 -0.0145 0.0105 1.0000
11.500 1.3118 0.01818 0.01241 -0.0137 0.0099 1.0000
11.750 1.3324 0.01877 0.01305 -0.0128 0.0094 1.0000
12.000 1.3523 0.01940 0.01373 -0.0119 0.0088 1.0000
12.250 1.3711 0.02011 0.01448 -0.0108 0.0083 1.0000
12.500 1.3890 0.02085 0.01530 -0.0096 0.0078 1.0000
12.750 1.4071 0.02152 0.01604 -0.0085 0.0076 1.0000
13.000 1.4241 0.02224 0.01683 -0.0072 0.0073 1.0000
13.250 1.4395 0.02301 0.01768 -0.0058 0.0070 1.0000
13.500 1.4517 0.02383 0.01857 -0.0038 0.0067 1.0000
13.750 1.4621 0.02474 0.01955 -0.0017 0.0065 1.0000
14.000 1.4713 0.02576 0.02065 0.0003 0.0063 1.0000
14.250 1.4787 0.02695 0.02193 0.0023 0.0060 1.0000
14.500 1.4842 0.02834 0.02341 0.0042 0.0058 1.0000
14.750 1.4893 0.02983 0.02500 0.0058 0.0057 1.0000
15.000 1.4949 0.03138 0.02665 0.0071 0.0056 1.0000
15.250 1.4991 0.03316 0.02854 0.0081 0.0055 1.0000
15.500 1.5018 0.03521 0.03070 0.0089 0.0054 1.0000
15.750 1.5030 0.03757 0.03318 0.0092 0.0054 1.0000
16.000 1.5023 0.04031 0.03604 0.0092 0.0053 1.0000
16.250 1.4999 0.04347 0.03932 0.0087 0.0052 1.0000
16.500 1.4951 0.04712 0.04311 0.0076 0.0051 1.0000
16.750 1.4877 0.05138 0.04750 0.0061 0.0051 1.0000
17.000 1.4772 0.05629 0.05255 0.0040 0.0050 1.0000
17.250 1.4630 0.06198 0.05838 0.0013 0.0050 1.0000
17.500 1.4444 0.06857 0.06513 -0.0020 0.0050 1.0000
17.750 1.4203 0.07629 0.07300 -0.0059 0.0050 1.0000
18.000 1.3905 0.08528 0.08217 -0.0106 0.0050 1.0000
18.250 1.3541 0.09577 0.09283 -0.0161 0.0050 1.0000
18.500 1.3107 0.10791 0.10516 -0.0224 0.0051 1.0000
18.750 1.2597 0.12204 0.11947 -0.0298 0.0052 1.0000
19.000 1.2059 0.13730 0.13492 -0.0380 0.0053 1.0000
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