NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 50,000 Max Cl/Cd: 18.75 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001035-il-50000-n5.txt Download as CSV file: xf-naca001035-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-35
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5833 0.11529 0.10814 -0.0280 1.0000 0.0599
-10.500 -0.5859 0.10958 0.10247 -0.0307 1.0000 0.0494
-10.250 -0.5905 0.10449 0.09744 -0.0329 1.0000 0.0468
-10.000 -0.6006 0.09831 0.09134 -0.0372 1.0000 0.0445
-9.750 -0.6225 0.09254 0.08558 -0.0412 1.0000 0.0428
-9.500 -0.6306 0.08882 0.08181 -0.0409 1.0000 0.0405
-9.250 -0.6414 0.08528 0.07828 -0.0395 1.0000 0.0398
-9.000 -0.6562 0.08218 0.07518 -0.0370 1.0000 0.0392
-8.750 -0.6718 0.07926 0.07224 -0.0338 1.0000 0.0386
-8.500 -0.6847 0.07607 0.06899 -0.0308 1.0000 0.0379
-8.250 -0.6964 0.07288 0.06570 -0.0275 1.0000 0.0371
-8.000 -0.7065 0.06963 0.06230 -0.0240 1.0000 0.0363
-7.750 -0.7150 0.06632 0.05880 -0.0202 1.0000 0.0354
-7.500 -0.7218 0.06297 0.05517 -0.0161 1.0000 0.0344
-7.250 -0.7263 0.05963 0.05144 -0.0117 1.0000 0.0333
-6.750 -0.7236 0.05381 0.04471 -0.0035 1.0000 0.0319
-6.500 -0.7179 0.05067 0.04124 -0.0001 1.0000 0.0317
-6.250 -0.7099 0.04766 0.03784 0.0031 1.0000 0.0317
-6.000 -0.6996 0.04502 0.03468 0.0065 1.0000 0.0321
-5.750 -0.6875 0.04191 0.03146 0.0085 1.0000 0.0339
-5.500 -0.6720 0.03953 0.02875 0.0107 1.0000 0.0360
-5.250 -0.6522 0.03704 0.02582 0.0127 1.0000 0.0372
-5.000 -0.6278 0.03459 0.02285 0.0141 1.0000 0.0383
-4.750 -0.5992 0.03244 0.02026 0.0149 1.0000 0.0406
-4.500 -0.5693 0.03036 0.01807 0.0148 1.0000 0.0467
-4.250 -0.5366 0.02872 0.01612 0.0148 1.0000 0.0522
-4.000 -0.5119 0.02731 0.01457 0.0155 1.0000 0.0630
-3.750 -0.2884 0.02623 0.01624 -0.0117 1.0000 0.9585
-3.500 -0.2417 0.02580 0.01523 -0.0163 1.0000 0.9731
-3.250 -0.2005 0.02533 0.01433 -0.0201 1.0000 0.9843
-3.000 -0.1602 0.02482 0.01348 -0.0238 1.0000 0.9939
-2.750 -0.1279 0.02438 0.01273 -0.0259 1.0000 1.0000
-2.500 -0.1160 0.02412 0.01233 -0.0237 1.0000 1.0000
-2.250 -0.1042 0.02389 0.01198 -0.0215 1.0000 1.0000
-2.000 -0.0924 0.02369 0.01167 -0.0193 1.0000 1.0000
-1.750 -0.0807 0.02352 0.01138 -0.0170 1.0000 1.0000
-1.500 -0.0691 0.02338 0.01115 -0.0146 1.0000 1.0000
-1.250 -0.0575 0.02326 0.01096 -0.0122 1.0000 1.0000
-1.000 -0.0459 0.02317 0.01081 -0.0098 1.0000 1.0000
-0.750 -0.0344 0.02309 0.01070 -0.0074 1.0000 1.0000
-0.500 -0.0229 0.02304 0.01061 -0.0049 1.0000 1.0000
-0.250 -0.0115 0.02301 0.01056 -0.0025 1.0000 1.0000
0.000 0.0000 0.02300 0.01054 0.0000 1.0000 1.0000
0.250 0.0115 0.02301 0.01055 0.0025 1.0000 1.0000
0.500 0.0229 0.02304 0.01060 0.0049 1.0000 1.0000
0.750 0.0344 0.02309 0.01070 0.0074 1.0000 1.0000
1.000 0.0459 0.02316 0.01081 0.0098 1.0000 1.0000
1.250 0.0575 0.02326 0.01096 0.0122 1.0000 1.0000
1.500 0.0691 0.02337 0.01115 0.0146 1.0000 1.0000
1.750 0.0807 0.02352 0.01137 0.0170 1.0000 1.0000
2.000 0.0924 0.02368 0.01166 0.0193 1.0000 1.0000
2.250 0.1042 0.02388 0.01197 0.0215 1.0000 1.0000
2.500 0.1161 0.02411 0.01232 0.0237 1.0000 1.0000
2.750 0.1280 0.02437 0.01272 0.0259 1.0000 1.0000
3.000 0.1601 0.02481 0.01347 0.0238 0.9940 1.0000
3.250 0.2005 0.02531 0.01432 0.0201 0.9844 1.0000
3.500 0.2416 0.02579 0.01522 0.0163 0.9732 1.0000
3.750 0.2882 0.02621 0.01623 0.0117 0.9586 1.0000
4.000 0.5119 0.02731 0.01456 -0.0155 0.0630 1.0000
4.250 0.5366 0.02872 0.01612 -0.0147 0.0522 1.0000
4.500 0.5693 0.03036 0.01807 -0.0148 0.0467 1.0000
4.750 0.5991 0.03243 0.02026 -0.0149 0.0406 1.0000
5.000 0.6277 0.03458 0.02284 -0.0141 0.0383 1.0000
5.250 0.6521 0.03704 0.02582 -0.0127 0.0372 1.0000
5.500 0.6720 0.03953 0.02875 -0.0107 0.0359 1.0000
5.750 0.6875 0.04190 0.03145 -0.0085 0.0339 1.0000
6.000 0.6996 0.04501 0.03467 -0.0065 0.0321 1.0000
6.250 0.7099 0.04765 0.03784 -0.0031 0.0317 1.0000
6.500 0.7178 0.05066 0.04123 0.0002 0.0317 1.0000
6.750 0.7236 0.05380 0.04470 0.0035 0.0319 1.0000
7.250 0.7263 0.05962 0.05143 0.0117 0.0333 1.0000
7.500 0.7218 0.06296 0.05516 0.0161 0.0344 1.0000
7.750 0.7150 0.06632 0.05880 0.0202 0.0354 1.0000
8.000 0.7066 0.06962 0.06230 0.0240 0.0363 1.0000
8.250 0.6965 0.07287 0.06569 0.0275 0.0371 1.0000
8.500 0.6849 0.07607 0.06899 0.0308 0.0379 1.0000
8.750 0.6719 0.07926 0.07224 0.0338 0.0386 1.0000
9.000 0.6564 0.08219 0.07519 0.0370 0.0392 1.0000
9.250 0.6417 0.08529 0.07829 0.0394 0.0398 1.0000
9.500 0.6310 0.08883 0.08182 0.0408 0.0405 1.0000
9.750 0.6226 0.09256 0.08561 0.0411 0.0429 1.0000
10.000 0.6010 0.09837 0.09139 0.0370 0.0446 1.0000
10.250 0.5910 0.10454 0.09749 0.0327 0.0468 1.0000
10.500 0.5866 0.10962 0.10250 0.0306 0.0494 1.0000
10.750 0.5839 0.11535 0.10820 0.0279 0.0601 1.0000
11.000 0.4640 0.10868 0.10194 0.0338 0.0467 1.0000
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Polar data table (+)
Polar graphs
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