NACA 1408 (naca1408-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 500,000 Max Cl/Cd: 62.33 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1408-il-500000-n5.txt Download as CSV file: xf-naca1408-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1408
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7983 0.09396 0.09175 0.0040 1.0000 0.0064
-11.750 -0.9559 0.04857 0.04613 -0.0313 1.0000 0.0053
-11.500 -0.9828 0.04162 0.03885 -0.0344 1.0000 0.0052
-11.250 -0.9881 0.03723 0.03414 -0.0347 1.0000 0.0053
-11.000 -0.9843 0.03389 0.03048 -0.0344 1.0000 0.0055
-10.750 -0.9755 0.03111 0.02738 -0.0338 1.0000 0.0057
-10.500 -0.9630 0.02875 0.02473 -0.0332 1.0000 0.0059
-10.250 -0.9479 0.02672 0.02238 -0.0325 1.0000 0.0061
-10.000 -0.9306 0.02500 0.02039 -0.0317 1.0000 0.0063
-9.750 -0.9145 0.02295 0.01807 -0.0309 1.0000 0.0065
-9.500 -0.8954 0.02149 0.01642 -0.0301 1.0000 0.0068
-9.250 -0.8742 0.02041 0.01521 -0.0295 1.0000 0.0071
-9.000 -0.8523 0.01946 0.01412 -0.0290 1.0000 0.0074
-8.750 -0.8300 0.01854 0.01306 -0.0283 1.0000 0.0078
-8.500 -0.8075 0.01766 0.01203 -0.0277 1.0000 0.0082
-8.250 -0.7848 0.01683 0.01107 -0.0270 1.0000 0.0087
-8.000 -0.7613 0.01619 0.01026 -0.0264 1.0000 0.0091
-7.750 -0.7393 0.01525 0.00924 -0.0256 1.0000 0.0101
-7.500 -0.7157 0.01471 0.00863 -0.0249 1.0000 0.0110
-7.250 -0.6922 0.01417 0.00802 -0.0242 1.0000 0.0118
-7.000 -0.6688 0.01365 0.00741 -0.0234 1.0000 0.0128
-6.750 -0.6456 0.01306 0.00675 -0.0226 1.0000 0.0141
-6.500 -0.6217 0.01268 0.00638 -0.0220 1.0000 0.0164
-6.250 -0.5976 0.01239 0.00603 -0.0213 1.0000 0.0186
-6.000 -0.5736 0.01207 0.00567 -0.0206 1.0000 0.0203
-5.750 -0.5500 0.01170 0.00529 -0.0198 1.0000 0.0233
-5.500 -0.5259 0.01148 0.00505 -0.0191 1.0000 0.0262
-5.250 -0.5018 0.01128 0.00481 -0.0184 1.0000 0.0283
-5.000 -0.4699 0.01102 0.00448 -0.0194 0.9980 0.0300
-4.750 -0.4362 0.01057 0.00402 -0.0209 0.9953 0.0336
-4.500 -0.4028 0.01029 0.00371 -0.0222 0.9922 0.0364
-4.250 -0.3690 0.01005 0.00343 -0.0236 0.9887 0.0387
-4.000 -0.3344 0.00978 0.00311 -0.0251 0.9859 0.0407
-3.750 -0.3025 0.00949 0.00281 -0.0260 0.9812 0.0439
-3.500 -0.2694 0.00924 0.00257 -0.0272 0.9767 0.0481
-3.250 -0.2382 0.00900 0.00234 -0.0280 0.9705 0.0572
-3.000 -0.2060 0.00869 0.00214 -0.0290 0.9645 0.0831
-2.750 -0.1762 0.00838 0.00196 -0.0295 0.9563 0.1155
-2.500 -0.1455 0.00811 0.00180 -0.0301 0.9482 0.1497
-2.250 -0.1163 0.00785 0.00166 -0.0304 0.9377 0.1874
-2.000 -0.0880 0.00758 0.00154 -0.0305 0.9258 0.2325
-1.500 -0.0337 0.00704 0.00133 -0.0302 0.8973 0.3421
-1.250 -0.0073 0.00680 0.00124 -0.0299 0.8806 0.4009
-1.000 0.0190 0.00660 0.00117 -0.0294 0.8622 0.4562
-0.750 0.0444 0.00632 0.00112 -0.0289 0.8417 0.5394
-0.500 0.0682 0.00593 0.00110 -0.0279 0.8194 0.6608
-0.250 0.0916 0.00567 0.00110 -0.0267 0.7946 0.7549
0.000 0.1158 0.00557 0.00111 -0.0256 0.7684 0.8121
0.250 0.1399 0.00554 0.00114 -0.0244 0.7419 0.8627
0.500 0.1650 0.00557 0.00117 -0.0234 0.7151 0.9066
0.750 0.1944 0.00567 0.00121 -0.0234 0.6858 0.9400
1.000 0.2267 0.00583 0.00124 -0.0242 0.6506 0.9632
1.250 0.2603 0.00608 0.00127 -0.0254 0.5980 0.9782
1.500 0.2938 0.00637 0.00132 -0.0268 0.5416 0.9889
1.750 0.3289 0.00669 0.00139 -0.0285 0.4795 0.9976
2.000 0.3572 0.00699 0.00146 -0.0288 0.4264 1.0000
2.250 0.3819 0.00728 0.00155 -0.0282 0.3776 1.0000
2.500 0.4067 0.00755 0.00166 -0.0277 0.3358 1.0000
2.750 0.4312 0.00791 0.00180 -0.0272 0.2833 1.0000
3.000 0.4554 0.00834 0.00197 -0.0266 0.2231 1.0000
3.250 0.4801 0.00873 0.00217 -0.0262 0.1758 1.0000
3.500 0.5049 0.00912 0.00239 -0.0257 0.1338 1.0000
3.750 0.5298 0.00953 0.00263 -0.0253 0.0964 1.0000
4.000 0.5549 0.00992 0.00289 -0.0248 0.0670 1.0000
4.250 0.5803 0.01028 0.00317 -0.0244 0.0491 1.0000
4.500 0.6062 0.01057 0.00345 -0.0241 0.0427 1.0000
4.750 0.6321 0.01086 0.00374 -0.0237 0.0396 1.0000
5.000 0.6578 0.01119 0.00409 -0.0233 0.0371 1.0000
5.250 0.6833 0.01156 0.00451 -0.0229 0.0346 1.0000
5.500 0.7094 0.01182 0.00481 -0.0226 0.0334 1.0000
5.750 0.7352 0.01212 0.00515 -0.0223 0.0316 1.0000
6.000 0.7609 0.01244 0.00551 -0.0220 0.0294 1.0000
6.250 0.7860 0.01286 0.00595 -0.0216 0.0269 1.0000
6.500 0.8109 0.01332 0.00647 -0.0211 0.0247 1.0000
6.750 0.8370 0.01354 0.00674 -0.0209 0.0228 1.0000
7.000 0.8627 0.01384 0.00709 -0.0206 0.0200 1.0000
7.250 0.8876 0.01427 0.00750 -0.0202 0.0170 1.0000
7.500 0.9123 0.01472 0.00803 -0.0198 0.0152 1.0000
7.750 0.9371 0.01514 0.00847 -0.0194 0.0132 1.0000
8.000 0.9609 0.01575 0.00908 -0.0188 0.0113 1.0000
8.250 0.9841 0.01642 0.00985 -0.0182 0.0105 1.0000
8.500 1.0073 0.01708 0.01061 -0.0176 0.0097 1.0000
8.750 1.0302 0.01776 0.01138 -0.0170 0.0090 1.0000
9.000 1.0529 0.01845 0.01214 -0.0163 0.0084 1.0000
9.250 1.0737 0.01942 0.01320 -0.0155 0.0076 1.0000
9.500 1.0947 0.02033 0.01427 -0.0147 0.0072 1.0000
9.750 1.1156 0.02122 0.01530 -0.0138 0.0068 1.0000
10.000 1.1355 0.02222 0.01645 -0.0129 0.0065 1.0000
10.250 1.1547 0.02328 0.01765 -0.0120 0.0062 1.0000
10.500 1.1732 0.02436 0.01887 -0.0110 0.0059 1.0000
10.750 1.1909 0.02549 0.02014 -0.0099 0.0057 1.0000
11.000 1.2071 0.02673 0.02151 -0.0088 0.0055 1.0000
11.250 1.2207 0.02820 0.02314 -0.0074 0.0053 1.0000
11.500 1.2291 0.03018 0.02532 -0.0056 0.0051 1.0000
11.750 1.2348 0.03231 0.02770 -0.0036 0.0050 1.0000
12.000 1.2394 0.03420 0.02981 -0.0015 0.0049 1.0000
12.250 1.2386 0.03626 0.03209 0.0009 0.0049 1.0000
12.500 1.2346 0.03870 0.03474 0.0029 0.0048 1.0000
12.750 1.2276 0.04167 0.03793 0.0041 0.0047 1.0000
13.000 1.2185 0.04531 0.04179 0.0040 0.0047 1.0000
13.250 1.2061 0.05001 0.04671 0.0023 0.0046 1.0000
13.500 1.1896 0.05623 0.05316 -0.0014 0.0046 1.0000
13.750 1.1699 0.06417 0.06131 -0.0071 0.0046 1.0000
14.000 1.1432 0.07450 0.07184 -0.0145 0.0047 1.0000
14.250 1.1092 0.08709 0.08460 -0.0227 0.0048 1.0000
14.500 1.0673 0.10158 0.09919 -0.0307 0.0049 1.0000
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