NACA 1408 (naca1408-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 100,000 Max Cl/Cd: 40.73 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1408-il-100000-n5.txt Download as CSV file: xf-naca1408-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6355 0.09008 0.08516 -0.0065 1.0000 0.0274
-9.250 -0.6419 0.08371 0.07884 -0.0108 1.0000 0.0273
-9.000 -0.6502 0.07643 0.07162 -0.0169 1.0000 0.0271
-8.750 -0.6621 0.06806 0.06322 -0.0243 1.0000 0.0266
-8.500 -0.6726 0.06059 0.05557 -0.0286 1.0000 0.0264
-8.250 -0.6795 0.05385 0.04853 -0.0310 1.0000 0.0264
-8.000 -0.6814 0.04769 0.04192 -0.0319 1.0000 0.0266
-7.750 -0.6778 0.04217 0.03583 -0.0318 1.0000 0.0271
-7.500 -0.6686 0.03742 0.03042 -0.0311 1.0000 0.0279
-7.250 -0.6545 0.03384 0.02615 -0.0301 1.0000 0.0296
-7.000 -0.6368 0.03174 0.02394 -0.0295 1.0000 0.0318
-6.750 -0.6173 0.02963 0.02146 -0.0286 1.0000 0.0339
-6.500 -0.5965 0.02741 0.01883 -0.0276 1.0000 0.0365
-6.250 -0.5746 0.02559 0.01657 -0.0266 1.0000 0.0401
-6.000 -0.5531 0.02397 0.01489 -0.0259 1.0000 0.0434
-5.750 -0.5302 0.02279 0.01352 -0.0251 1.0000 0.0478
-5.500 -0.5071 0.02157 0.01206 -0.0241 1.0000 0.0523
-5.250 -0.4848 0.02044 0.01090 -0.0233 1.0000 0.0565
-5.000 -0.4616 0.01966 0.00998 -0.0225 1.0000 0.0626
-4.750 -0.4390 0.01866 0.00892 -0.0215 1.0000 0.0665
-4.500 -0.4164 0.01786 0.00810 -0.0206 1.0000 0.0712
-4.250 -0.3931 0.01724 0.00737 -0.0197 1.0000 0.0783
-4.000 -0.3703 0.01654 0.00669 -0.0189 1.0000 0.0891
-3.750 -0.3472 0.01585 0.00603 -0.0181 1.0000 0.1033
-3.500 -0.3240 0.01517 0.00549 -0.0174 1.0000 0.1308
-3.250 -0.3007 0.01456 0.00507 -0.0168 1.0000 0.1783
-3.000 -0.2774 0.01400 0.00474 -0.0162 1.0000 0.2397
-2.750 -0.2543 0.01339 0.00452 -0.0157 1.0000 0.3286
-2.500 -0.2323 0.01261 0.00440 -0.0148 1.0000 0.4696
-2.250 -0.2113 0.01198 0.00436 -0.0133 1.0000 0.6117
-2.000 -0.1902 0.01161 0.00436 -0.0113 1.0000 0.7201
-1.750 -0.1674 0.01141 0.00443 -0.0092 1.0000 0.8272
-1.500 -0.1264 0.01138 0.00443 -0.0111 1.0000 0.9320
-1.250 -0.0743 0.01137 0.00430 -0.0162 1.0000 1.0000
-1.000 -0.0574 0.01141 0.00423 -0.0146 1.0000 1.0000
-0.750 -0.0301 0.01148 0.00418 -0.0150 0.9965 1.0000
-0.500 0.0124 0.01155 0.00416 -0.0184 0.9870 1.0000
-0.250 0.0545 0.01160 0.00413 -0.0217 0.9767 1.0000
0.000 0.0961 0.01162 0.00411 -0.0247 0.9656 1.0000
0.250 0.1360 0.01164 0.00410 -0.0273 0.9531 1.0000
0.500 0.1739 0.01163 0.00409 -0.0294 0.9389 1.0000
0.750 0.2108 0.01162 0.00408 -0.0312 0.9234 1.0000
1.000 0.2453 0.01160 0.00408 -0.0324 0.9054 1.0000
1.250 0.2775 0.01159 0.00408 -0.0329 0.8843 1.0000
1.500 0.3090 0.01157 0.00408 -0.0333 0.8619 1.0000
1.750 0.3386 0.01158 0.00409 -0.0332 0.8370 1.0000
2.000 0.3664 0.01161 0.00412 -0.0326 0.8093 1.0000
2.250 0.3933 0.01167 0.00416 -0.0319 0.7791 1.0000
2.500 0.4191 0.01177 0.00424 -0.0309 0.7448 1.0000
2.750 0.4445 0.01192 0.00432 -0.0299 0.7081 1.0000
3.000 0.4691 0.01212 0.00443 -0.0287 0.6677 1.0000
3.250 0.4931 0.01238 0.00458 -0.0275 0.6219 1.0000
3.500 0.5161 0.01272 0.00473 -0.0261 0.5658 1.0000
3.750 0.5377 0.01320 0.00489 -0.0246 0.4900 1.0000
4.000 0.5584 0.01385 0.00510 -0.0232 0.3967 1.0000
4.250 0.5799 0.01458 0.00546 -0.0221 0.3073 1.0000
4.500 0.6015 0.01543 0.00592 -0.0213 0.2240 1.0000
4.750 0.6230 0.01640 0.00654 -0.0205 0.1503 1.0000
5.000 0.6449 0.01740 0.00730 -0.0197 0.1052 1.0000
5.250 0.6670 0.01836 0.00819 -0.0188 0.0861 1.0000
5.500 0.6898 0.01921 0.00911 -0.0179 0.0765 1.0000
5.750 0.7118 0.02013 0.01006 -0.0171 0.0688 1.0000
6.000 0.7344 0.02098 0.01101 -0.0162 0.0626 1.0000
6.250 0.7551 0.02222 0.01224 -0.0152 0.0585 1.0000
6.500 0.7783 0.02315 0.01339 -0.0144 0.0534 1.0000
6.750 0.8005 0.02425 0.01456 -0.0136 0.0487 1.0000
7.000 0.8218 0.02582 0.01618 -0.0127 0.0446 1.0000
7.250 0.8445 0.02713 0.01774 -0.0118 0.0401 1.0000
7.500 0.8660 0.02868 0.01941 -0.0110 0.0369 1.0000
7.750 0.8861 0.03076 0.02165 -0.0102 0.0337 1.0000
8.000 0.9065 0.03289 0.02424 -0.0090 0.0311 1.0000
8.250 0.9248 0.03534 0.02707 -0.0079 0.0291 1.0000
8.500 0.9414 0.03731 0.02929 -0.0068 0.0270 1.0000
8.750 0.9550 0.03986 0.03195 -0.0059 0.0253 1.0000
9.000 0.9644 0.04316 0.03582 -0.0042 0.0243 1.0000
9.250 0.9684 0.04713 0.04036 -0.0024 0.0236 1.0000
9.500 0.9667 0.05147 0.04521 -0.0007 0.0232 1.0000
9.750 0.9590 0.05600 0.05016 0.0009 0.0229 1.0000
10.000 0.9454 0.06048 0.05498 0.0021 0.0228 1.0000
10.250 0.9263 0.06488 0.05962 0.0029 0.0229 1.0000
10.500 0.9056 0.07017 0.06509 0.0011 0.0230 1.0000
10.750 0.8841 0.07693 0.07201 -0.0036 0.0232 1.0000
11.000 0.8627 0.08573 0.08092 -0.0109 0.0236 1.0000
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Polar data table (+)
Polar graphs
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