NACA 1408 (naca1408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.72 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1408-il-1000000.txt Download as CSV file: xf-naca1408-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6537 0.14352 0.14182 0.0249 1.0000 0.0115
-12.250 -0.6503 0.13947 0.13777 0.0232 1.0000 0.0119
-11.750 -1.0026 0.04092 0.03869 -0.0352 1.0000 0.0072
-11.250 -1.0342 0.02891 0.02570 -0.0345 1.0000 0.0075
-11.000 -1.0246 0.02620 0.02272 -0.0336 1.0000 0.0078
-10.750 -1.0066 0.02485 0.02123 -0.0330 1.0000 0.0080
-10.500 -0.9868 0.02372 0.01997 -0.0324 1.0000 0.0083
-10.250 -0.9669 0.02253 0.01865 -0.0319 1.0000 0.0085
-10.000 -0.9464 0.02136 0.01732 -0.0312 1.0000 0.0088
-9.750 -0.9256 0.02018 0.01597 -0.0306 1.0000 0.0091
-9.500 -0.9043 0.01909 0.01471 -0.0299 1.0000 0.0094
-9.250 -0.8820 0.01815 0.01363 -0.0293 1.0000 0.0097
-9.000 -0.8589 0.01741 0.01277 -0.0287 1.0000 0.0100
-8.750 -0.8395 0.01580 0.01092 -0.0276 1.0000 0.0105
-8.500 -0.8176 0.01483 0.00986 -0.0268 1.0000 0.0111
-8.250 -0.7936 0.01438 0.00936 -0.0263 1.0000 0.0117
-8.000 -0.7695 0.01399 0.00893 -0.0257 1.0000 0.0123
-7.750 -0.7455 0.01361 0.00849 -0.0250 1.0000 0.0130
-7.500 -0.7214 0.01326 0.00809 -0.0243 1.0000 0.0135
-7.250 -0.7001 0.01227 0.00698 -0.0232 1.0000 0.0145
-7.000 -0.6766 0.01185 0.00655 -0.0225 1.0000 0.0155
-6.750 -0.6526 0.01159 0.00627 -0.0217 1.0000 0.0164
-6.500 -0.6288 0.01132 0.00597 -0.0209 1.0000 0.0175
-6.250 -0.6047 0.01116 0.00578 -0.0202 1.0000 0.0182
-6.000 -0.5826 0.01048 0.00506 -0.0192 1.0000 0.0203
-5.750 -0.5587 0.01030 0.00489 -0.0184 1.0000 0.0218
-5.500 -0.5350 0.01011 0.00468 -0.0176 1.0000 0.0233
-5.250 -0.5111 0.01000 0.00455 -0.0168 1.0000 0.0243
-5.000 -0.4811 0.00936 0.00386 -0.0175 0.9991 0.0272
-4.750 -0.4464 0.00912 0.00362 -0.0191 0.9974 0.0296
-4.500 -0.4114 0.00889 0.00337 -0.0207 0.9957 0.0315
-4.250 -0.3758 0.00874 0.00321 -0.0224 0.9943 0.0326
-4.000 -0.3430 0.00825 0.00267 -0.0235 0.9917 0.0368
-3.750 -0.3090 0.00800 0.00243 -0.0249 0.9891 0.0398
-3.500 -0.2739 0.00781 0.00222 -0.0265 0.9868 0.0423
-3.250 -0.2383 0.00752 0.00196 -0.0282 0.9849 0.0503
-3.000 -0.2050 0.00713 0.00175 -0.0295 0.9818 0.0874
-2.750 -0.1747 0.00675 0.00158 -0.0301 0.9760 0.1378
-2.500 -0.1429 0.00642 0.00143 -0.0311 0.9711 0.1901
-2.250 -0.1149 0.00611 0.00132 -0.0312 0.9627 0.2433
-2.000 -0.0864 0.00580 0.00121 -0.0313 0.9543 0.3059
-1.750 -0.0599 0.00552 0.00112 -0.0310 0.9431 0.3676
-1.500 -0.0341 0.00520 0.00104 -0.0305 0.9304 0.4461
-1.250 -0.0084 0.00492 0.00097 -0.0300 0.9160 0.5213
-1.000 0.0172 0.00470 0.00092 -0.0294 0.8996 0.5891
-0.750 0.0426 0.00447 0.00088 -0.0287 0.8814 0.6636
-0.500 0.0669 0.00419 0.00087 -0.0278 0.8612 0.7582
-0.250 0.0912 0.00404 0.00087 -0.0267 0.8402 0.8254
0.000 0.1147 0.00394 0.00090 -0.0253 0.8170 0.8871
0.250 0.1386 0.00395 0.00092 -0.0240 0.7919 0.9321
0.500 0.1664 0.00404 0.00094 -0.0237 0.7628 0.9582
0.750 0.1987 0.00417 0.00096 -0.0245 0.7305 0.9751
1.000 0.2329 0.00433 0.00098 -0.0258 0.6947 0.9863
1.250 0.2680 0.00460 0.00101 -0.0274 0.6342 0.9935
1.500 0.3052 0.00488 0.00105 -0.0295 0.5749 0.9978
2.000 0.3626 0.00525 0.00114 -0.0300 0.4987 1.0000
2.250 0.3881 0.00544 0.00120 -0.0296 0.4624 1.0000
2.500 0.4131 0.00571 0.00128 -0.0290 0.4141 1.0000
2.750 0.4378 0.00602 0.00138 -0.0285 0.3592 1.0000
3.000 0.4623 0.00638 0.00151 -0.0279 0.3001 1.0000
3.250 0.4865 0.00680 0.00167 -0.0273 0.2380 1.0000
3.500 0.5105 0.00729 0.00188 -0.0268 0.1720 1.0000
3.750 0.5345 0.00783 0.00214 -0.0262 0.1065 1.0000
4.000 0.5585 0.00841 0.00244 -0.0256 0.0513 1.0000
4.250 0.5842 0.00874 0.00270 -0.0251 0.0413 1.0000
4.500 0.6105 0.00896 0.00294 -0.0248 0.0388 1.0000
4.750 0.6368 0.00919 0.00320 -0.0245 0.0365 1.0000
5.000 0.6628 0.00950 0.00350 -0.0241 0.0337 1.0000
5.250 0.6880 0.00998 0.00403 -0.0236 0.0304 1.0000
5.500 0.7145 0.01019 0.00427 -0.0234 0.0296 1.0000
5.750 0.7408 0.01043 0.00453 -0.0231 0.0280 1.0000
6.000 0.7670 0.01069 0.00480 -0.0228 0.0261 1.0000
6.250 0.7918 0.01123 0.00535 -0.0224 0.0235 1.0000
6.500 0.8170 0.01167 0.00585 -0.0219 0.0221 1.0000
6.750 0.8435 0.01188 0.00608 -0.0217 0.0208 1.0000
7.000 0.8698 0.01209 0.00629 -0.0215 0.0192 1.0000
7.250 0.8938 0.01273 0.00694 -0.0210 0.0171 1.0000
7.500 0.9192 0.01311 0.00736 -0.0206 0.0163 1.0000
7.750 0.9448 0.01343 0.00773 -0.0203 0.0153 1.0000
8.000 0.9703 0.01376 0.00808 -0.0199 0.0143 1.0000
8.250 0.9950 0.01421 0.00854 -0.0195 0.0133 1.0000
8.500 1.0166 0.01519 0.00961 -0.0187 0.0123 1.0000
8.750 1.0416 0.01555 0.01002 -0.0183 0.0117 1.0000
9.000 1.0658 0.01604 0.01058 -0.0178 0.0111 1.0000
9.250 1.0897 0.01655 0.01114 -0.0173 0.0105 1.0000
9.500 1.1132 0.01710 0.01173 -0.0168 0.0100 1.0000
9.750 1.1329 0.01823 0.01295 -0.0158 0.0094 1.0000
10.000 1.1505 0.01972 0.01462 -0.0145 0.0090 1.0000
10.250 1.1722 0.02046 0.01547 -0.0138 0.0088 1.0000
10.500 1.1927 0.02136 0.01650 -0.0129 0.0085 1.0000
10.750 1.2120 0.02238 0.01765 -0.0119 0.0082 1.0000
11.000 1.2306 0.02343 0.01883 -0.0109 0.0079 1.0000
11.250 1.2486 0.02448 0.02000 -0.0099 0.0077 1.0000
11.500 1.2668 0.02539 0.02100 -0.0089 0.0074 1.0000
11.750 1.2844 0.02629 0.02198 -0.0079 0.0072 1.0000
12.000 1.2986 0.02752 0.02332 -0.0066 0.0069 1.0000
12.250 1.3005 0.03006 0.02611 -0.0042 0.0066 1.0000
12.500 1.2808 0.03419 0.03063 0.0002 0.0064 1.0000
12.750 1.2823 0.03589 0.03248 0.0024 0.0064 1.0000
13.000 1.2812 0.03797 0.03472 0.0040 0.0063 1.0000
13.250 1.2749 0.04085 0.03778 0.0049 0.0063 1.0000
13.500 1.2657 0.04453 0.04165 0.0046 0.0062 1.0000
13.750 1.2538 0.04921 0.04651 0.0028 0.0062 1.0000
14.000 1.2353 0.05582 0.05333 -0.0012 0.0062 1.0000
14.250 1.2119 0.06441 0.06212 -0.0073 0.0062 1.0000
14.500 1.1775 0.07621 0.07412 -0.0157 0.0063 1.0000
14.750 1.0232 0.07504 0.07294 -0.0041 0.0067 1.0000
15.000 0.9988 0.08384 0.08184 -0.0075 0.0068 1.0000
15.250 0.9475 0.09793 0.09613 -0.0134 0.0070 1.0000
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Polar data table (+)
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