NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 100,000 Max Cl/Cd: 30.09 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca000834-il-100000-n5.txt Download as CSV file: xf-naca000834-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008-34
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 -0.5190 0.09074 0.08620 -0.0148 1.0000 0.0483
-9.250 -0.5249 0.08592 0.08141 -0.0166 1.0000 0.0487
-9.000 -0.5326 0.08082 0.07635 -0.0188 1.0000 0.0490
-8.750 -0.5428 0.07535 0.07090 -0.0218 1.0000 0.0493
-8.500 -0.5577 0.06966 0.06523 -0.0257 1.0000 0.0495
-8.250 -0.5743 0.06497 0.06050 -0.0274 1.0000 0.0497
-8.000 -0.5904 0.06090 0.05638 -0.0271 1.0000 0.0499
-7.500 -0.6126 0.05027 0.04531 -0.0254 1.0000 0.0328
-7.250 -0.6142 0.04494 0.03991 -0.0240 1.0000 0.0275
-7.000 -0.6598 0.05371 0.04795 -0.0187 1.0000 0.0222
-6.750 -0.6535 0.04974 0.04373 -0.0171 1.0000 0.0207
-6.500 -0.6449 0.04577 0.03936 -0.0151 1.0000 0.0191
-6.250 -0.6340 0.04177 0.03489 -0.0125 1.0000 0.0176
-6.000 -0.6193 0.03831 0.03080 -0.0095 1.0000 0.0162
-5.750 -0.6022 0.03594 0.02798 -0.0072 1.0000 0.0157
-4.750 -0.5275 0.02534 0.01593 -0.0001 1.0000 0.0171
-4.500 -0.5056 0.02364 0.01405 0.0011 1.0000 0.0191
-4.250 -0.4826 0.02188 0.01210 0.0025 1.0000 0.0201
-4.000 -0.4612 0.02034 0.01039 0.0041 1.0000 0.0213
-3.750 -0.4414 0.01913 0.00904 0.0059 1.0000 0.0234
-3.500 -0.4232 0.01794 0.00779 0.0076 1.0000 0.0281
-3.250 -0.4031 0.01705 0.00668 0.0093 1.0000 0.0330
-3.000 -0.3829 0.01605 0.00566 0.0108 1.0000 0.0505
-2.750 -0.3766 0.01252 0.00490 0.0139 1.0000 0.5745
-2.500 -0.3383 0.01283 0.00615 0.0171 1.0000 0.9063
-2.250 -0.3029 0.01293 0.00592 0.0158 1.0000 0.9278
-2.000 -0.2638 0.01299 0.00569 0.0135 1.0000 0.9424
-1.750 -0.2245 0.01301 0.00544 0.0109 1.0000 0.9553
-1.500 -0.1824 0.01300 0.00523 0.0076 1.0000 0.9657
-1.250 -0.1395 0.01297 0.00500 0.0040 1.0000 0.9747
-1.000 -0.0977 0.01291 0.00483 0.0005 1.0000 0.9838
-0.750 -0.0558 0.01284 0.00467 -0.0031 1.0000 0.9925
-0.500 -0.0159 0.01275 0.00453 -0.0063 1.0000 1.0000
-0.250 -0.0076 0.01270 0.00447 -0.0032 1.0000 1.0000
0.000 0.0000 0.01268 0.00445 0.0000 1.0000 1.0000
0.250 0.0076 0.01270 0.00447 0.0032 1.0000 1.0000
0.500 0.0159 0.01275 0.00453 0.0063 1.0000 1.0000
0.750 0.0557 0.01283 0.00467 0.0031 0.9925 1.0000
1.000 0.0976 0.01291 0.00482 -0.0005 0.9839 1.0000
1.250 0.1394 0.01296 0.00500 -0.0040 0.9747 1.0000
1.500 0.1824 0.01300 0.00522 -0.0076 0.9657 1.0000
1.750 0.2244 0.01301 0.00543 -0.0109 0.9553 1.0000
2.000 0.2637 0.01299 0.00568 -0.0135 0.9425 1.0000
2.250 0.3027 0.01293 0.00592 -0.0158 0.9278 1.0000
2.500 0.3381 0.01283 0.00614 -0.0171 0.9063 1.0000
2.750 0.3764 0.01251 0.00490 -0.0139 0.5767 1.0000
3.000 0.3826 0.01604 0.00565 -0.0107 0.0507 1.0000
3.250 0.4028 0.01704 0.00667 -0.0092 0.0330 1.0000
3.500 0.4229 0.01793 0.00778 -0.0076 0.0281 1.0000
3.750 0.4411 0.01912 0.00904 -0.0059 0.0234 1.0000
4.000 0.4609 0.02033 0.01038 -0.0041 0.0213 1.0000
4.250 0.4824 0.02187 0.01209 -0.0025 0.0201 1.0000
4.500 0.5054 0.02363 0.01404 -0.0011 0.0191 1.0000
4.750 0.5273 0.02533 0.01593 0.0002 0.0171 1.0000
5.000 0.5470 0.02813 0.01897 0.0015 0.0156 1.0000
5.500 0.5847 0.03352 0.02515 0.0052 0.0155 1.0000
5.750 0.6021 0.03593 0.02796 0.0073 0.0157 1.0000
6.000 0.6193 0.03831 0.03079 0.0096 0.0162 1.0000
6.250 0.6340 0.04177 0.03488 0.0125 0.0176 1.0000
6.500 0.6450 0.04577 0.03936 0.0151 0.0191 1.0000
6.750 0.6536 0.04975 0.04374 0.0171 0.0207 1.0000
7.000 0.6600 0.05372 0.04796 0.0187 0.0222 1.0000
7.250 0.6710 0.06096 0.05568 0.0207 0.0499 1.0000
7.500 0.6733 0.06498 0.05995 0.0213 0.0492 1.0000
7.750 0.6737 0.06899 0.06411 0.0216 0.0481 1.0000
8.000 0.6727 0.07298 0.06820 0.0215 0.0471 1.0000
8.250 0.6717 0.07689 0.07216 0.0215 0.0460 1.0000
9.250 0.5246 0.08582 0.08130 0.0166 0.0487 1.0000
9.500 0.5186 0.09064 0.08609 0.0148 0.0483 1.0000
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Polar data table (+)
Polar graphs
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