NACA 0010-34 (naca001034-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-34 (naca001034-il) Reynolds number: 100,000 Max Cl/Cd: 34.83 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001034-il-100000-n5.txt Download as CSV file: xf-naca001034-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-34
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6212 0.10454 0.09963 -0.0161 1.0000 0.0198
-10.500 -0.6241 0.09935 0.09448 -0.0184 1.0000 0.0194
-10.250 -0.6283 0.09334 0.08850 -0.0218 1.0000 0.0190
-10.000 -0.6353 0.08637 0.08154 -0.0269 1.0000 0.0187
-9.750 -0.6468 0.08021 0.07535 -0.0313 1.0000 0.0185
-9.500 -0.6612 0.07509 0.07017 -0.0338 1.0000 0.0183
-9.250 -0.6767 0.07087 0.06585 -0.0343 1.0000 0.0181
-9.000 -0.6923 0.06730 0.06218 -0.0329 1.0000 0.0180
-8.750 -0.7049 0.06380 0.05854 -0.0309 1.0000 0.0177
-8.500 -0.7136 0.06019 0.05474 -0.0287 1.0000 0.0175
-8.250 -0.7194 0.05660 0.05092 -0.0262 1.0000 0.0172
-8.000 -0.7225 0.05305 0.04712 -0.0234 1.0000 0.0170
-7.750 -0.7232 0.04961 0.04337 -0.0203 1.0000 0.0167
-7.500 -0.7213 0.04630 0.03974 -0.0171 1.0000 0.0165
-7.250 -0.7170 0.04313 0.03613 -0.0139 1.0000 0.0164
-7.000 -0.7100 0.04021 0.03282 -0.0107 1.0000 0.0166
-6.750 -0.7002 0.03756 0.02976 -0.0078 1.0000 0.0173
-6.500 -0.6879 0.03508 0.02686 -0.0050 1.0000 0.0182
-6.250 -0.6730 0.03269 0.02404 -0.0024 1.0000 0.0187
-6.000 -0.6555 0.03032 0.02129 -0.0002 1.0000 0.0189
-5.750 -0.6356 0.02817 0.01880 0.0017 1.0000 0.0193
-5.500 -0.6144 0.02629 0.01665 0.0033 1.0000 0.0199
-5.250 -0.5937 0.02457 0.01475 0.0048 1.0000 0.0210
-5.000 -0.5765 0.02292 0.01311 0.0065 1.0000 0.0238
-4.750 -0.5594 0.02171 0.01182 0.0085 1.0000 0.0260
-4.500 -0.5434 0.02062 0.01055 0.0108 1.0000 0.0282
-4.250 -0.5274 0.01965 0.00945 0.0130 1.0000 0.0323
-4.000 -0.5100 0.01884 0.00850 0.0148 1.0000 0.0392
-3.750 -0.4926 0.01785 0.00750 0.0167 1.0000 0.0544
-3.500 -0.4818 0.01554 0.00652 0.0189 1.0000 0.2814
-3.250 -0.4749 0.01364 0.00653 0.0232 1.0000 0.6422
-3.000 -0.4554 0.01387 0.00729 0.0276 1.0000 0.8092
-2.750 -0.4303 0.01420 0.00749 0.0293 1.0000 0.8534
-2.500 -0.4030 0.01436 0.00744 0.0296 1.0000 0.8738
-2.250 -0.3740 0.01452 0.00738 0.0295 1.0000 0.8917
-2.000 -0.3442 0.01467 0.00735 0.0290 1.0000 0.9077
-1.750 -0.3123 0.01482 0.00733 0.0280 1.0000 0.9218
-1.500 -0.2756 0.01497 0.00733 0.0258 0.9991 0.9334
-1.250 -0.2318 0.01512 0.00730 0.0221 0.9959 0.9428
-1.000 -0.1887 0.01524 0.00730 0.0184 0.9920 0.9522
-0.750 -0.1403 0.01535 0.00729 0.0136 0.9890 0.9580
-0.500 -0.0950 0.01544 0.00731 0.0094 0.9852 0.9658
-0.250 -0.0466 0.01547 0.00730 0.0045 0.9809 0.9706
0.000 0.0000 0.01551 0.00732 0.0000 0.9769 0.9769
0.250 0.0467 0.01547 0.00730 -0.0046 0.9706 0.9809
0.500 0.0951 0.01544 0.00731 -0.0094 0.9658 0.9853
0.750 0.1403 0.01535 0.00729 -0.0136 0.9580 0.9890
1.000 0.1888 0.01524 0.00729 -0.0185 0.9522 0.9921
1.250 0.2318 0.01512 0.00730 -0.0221 0.9429 0.9959
1.500 0.2757 0.01497 0.00732 -0.0259 0.9335 0.9991
1.750 0.3123 0.01482 0.00733 -0.0280 0.9218 1.0000
2.000 0.3441 0.01467 0.00735 -0.0290 0.9077 1.0000
2.250 0.3739 0.01452 0.00738 -0.0295 0.8917 1.0000
2.500 0.4030 0.01436 0.00744 -0.0296 0.8738 1.0000
2.750 0.4302 0.01420 0.00749 -0.0292 0.8534 1.0000
3.000 0.4553 0.01386 0.00728 -0.0276 0.8094 1.0000
3.250 0.4748 0.01363 0.00652 -0.0232 0.6437 1.0000
3.500 0.4817 0.01553 0.00652 -0.0189 0.2833 1.0000
3.750 0.4925 0.01784 0.00749 -0.0167 0.0545 1.0000
4.000 0.5099 0.01884 0.00850 -0.0148 0.0393 1.0000
4.250 0.5273 0.01965 0.00944 -0.0129 0.0324 1.0000
4.500 0.5433 0.02061 0.01054 -0.0108 0.0282 1.0000
4.750 0.5593 0.02170 0.01181 -0.0085 0.0260 1.0000
5.000 0.5763 0.02292 0.01311 -0.0065 0.0238 1.0000
5.250 0.5936 0.02456 0.01475 -0.0048 0.0210 1.0000
5.500 0.6143 0.02629 0.01664 -0.0033 0.0199 1.0000
5.750 0.6355 0.02817 0.01880 -0.0016 0.0193 1.0000
6.000 0.6554 0.03032 0.02128 0.0002 0.0189 1.0000
6.250 0.6729 0.03268 0.02403 0.0024 0.0187 1.0000
6.500 0.6878 0.03508 0.02685 0.0050 0.0182 1.0000
6.750 0.7002 0.03755 0.02975 0.0078 0.0173 1.0000
7.000 0.7100 0.04021 0.03282 0.0108 0.0166 1.0000
7.250 0.7170 0.04313 0.03613 0.0139 0.0164 1.0000
7.500 0.7213 0.04630 0.03974 0.0171 0.0165 1.0000
7.750 0.7232 0.04962 0.04338 0.0203 0.0167 1.0000
8.000 0.7226 0.05307 0.04713 0.0233 0.0170 1.0000
8.250 0.7195 0.05661 0.05094 0.0261 0.0172 1.0000
8.500 0.7137 0.06021 0.05477 0.0286 0.0175 1.0000
8.750 0.7051 0.06384 0.05858 0.0308 0.0177 1.0000
9.000 0.6926 0.06733 0.06222 0.0328 0.0180 1.0000
9.250 0.6770 0.07091 0.06590 0.0342 0.0181 1.0000
9.500 0.6616 0.07515 0.07022 0.0337 0.0183 1.0000
9.750 0.6473 0.08029 0.07543 0.0311 0.0185 1.0000
10.000 0.6358 0.08647 0.08165 0.0267 0.0187 1.0000
10.250 0.6290 0.09343 0.08859 0.0216 0.0190 1.0000
10.500 0.6249 0.09944 0.09456 0.0182 0.0194 1.0000
10.750 0.6221 0.10462 0.09971 0.0159 0.0198 1.0000
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Polar data table (+)
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