NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 100,000 Max Cl/Cd: 36.72 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001234-il-100000-n5.txt Download as CSV file: xf-naca001234-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-34
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6411 0.08921 0.08427 -0.0362 1.0000 0.0199
-11.000 -0.6607 0.08149 0.07649 -0.0414 1.0000 0.0195
-10.750 -0.6820 0.07531 0.07020 -0.0446 1.0000 0.0191
-10.500 -0.7031 0.07030 0.06506 -0.0458 1.0000 0.0188
-10.250 -0.7230 0.06622 0.06083 -0.0452 1.0000 0.0187
-10.000 -0.7420 0.06276 0.05721 -0.0431 1.0000 0.0185
-9.750 -0.7600 0.05983 0.05411 -0.0395 1.0000 0.0185
-9.500 -0.7756 0.05706 0.05115 -0.0353 1.0000 0.0185
-9.250 -0.7869 0.05416 0.04801 -0.0312 1.0000 0.0185
-9.000 -0.7955 0.05127 0.04485 -0.0270 1.0000 0.0185
-8.750 -0.8013 0.04838 0.04166 -0.0227 1.0000 0.0184
-8.500 -0.8038 0.04554 0.03849 -0.0186 1.0000 0.0184
-8.250 -0.8031 0.04281 0.03540 -0.0146 1.0000 0.0184
-8.000 -0.7991 0.04019 0.03242 -0.0109 1.0000 0.0185
-7.750 -0.7916 0.03769 0.02956 -0.0076 1.0000 0.0187
-7.500 -0.7805 0.03534 0.02685 -0.0047 1.0000 0.0191
-7.250 -0.7665 0.03323 0.02434 -0.0022 1.0000 0.0198
-7.000 -0.7506 0.03147 0.02229 0.0000 1.0000 0.0214
-6.750 -0.7323 0.02979 0.02033 0.0019 1.0000 0.0228
-6.500 -0.7129 0.02814 0.01847 0.0036 1.0000 0.0237
-6.250 -0.6950 0.02675 0.01692 0.0055 1.0000 0.0246
-6.000 -0.6820 0.02518 0.01534 0.0080 1.0000 0.0262
-5.750 -0.6698 0.02417 0.01433 0.0105 1.0000 0.0291
-5.500 -0.6573 0.02325 0.01330 0.0132 1.0000 0.0322
-5.250 -0.6449 0.02237 0.01226 0.0159 1.0000 0.0347
-5.000 -0.6327 0.02142 0.01121 0.0185 1.0000 0.0402
-4.750 -0.6186 0.02056 0.01029 0.0208 1.0000 0.0495
-4.500 -0.6043 0.01958 0.00940 0.0231 1.0000 0.0733
-4.250 -0.5972 0.01752 0.00850 0.0258 1.0000 0.2575
-4.000 -0.5828 0.01587 0.00813 0.0276 0.9973 0.4949
-3.750 -0.5591 0.01537 0.00845 0.0292 0.9940 0.6666
-3.500 -0.5310 0.01563 0.00890 0.0305 0.9900 0.7561
-3.250 -0.4964 0.01587 0.00898 0.0295 0.9865 0.7857
-3.000 -0.4626 0.01604 0.00898 0.0284 0.9821 0.8050
-2.750 -0.4273 0.01622 0.00896 0.0269 0.9781 0.8232
-2.500 -0.3926 0.01639 0.00897 0.0255 0.9738 0.8389
-2.250 -0.3574 0.01656 0.00899 0.0239 0.9691 0.8521
-2.000 -0.3178 0.01675 0.00903 0.0214 0.9657 0.8631
-1.750 -0.2826 0.01690 0.00906 0.0198 0.9605 0.8736
-1.500 -0.2459 0.01702 0.00907 0.0178 0.9556 0.8839
-1.250 -0.2034 0.01717 0.00911 0.0145 0.9523 0.8920
-1.000 -0.1670 0.01728 0.00915 0.0126 0.9465 0.9001
-0.750 -0.1289 0.01735 0.00915 0.0102 0.9413 0.9090
-0.250 -0.0453 0.01750 0.00923 0.0039 0.9314 0.9218
0.000 0.0000 0.01751 0.00923 0.0000 0.9268 0.9268
0.250 0.0453 0.01749 0.00923 -0.0039 0.9218 0.9314
0.750 0.1290 0.01734 0.00915 -0.0102 0.9090 0.9413
1.000 0.1670 0.01728 0.00915 -0.0126 0.9001 0.9465
1.250 0.2034 0.01716 0.00911 -0.0145 0.8921 0.9524
1.500 0.2459 0.01701 0.00907 -0.0178 0.8839 0.9556
1.750 0.2826 0.01690 0.00906 -0.0198 0.8736 0.9606
2.000 0.3178 0.01675 0.00903 -0.0214 0.8631 0.9657
2.250 0.3574 0.01655 0.00899 -0.0239 0.8521 0.9691
2.500 0.3926 0.01638 0.00896 -0.0255 0.8389 0.9738
2.750 0.4273 0.01622 0.00896 -0.0269 0.8232 0.9781
3.000 0.4626 0.01604 0.00898 -0.0284 0.8050 0.9822
3.250 0.4964 0.01587 0.00898 -0.0295 0.7857 0.9866
3.500 0.5310 0.01563 0.00890 -0.0305 0.7561 0.9901
3.750 0.5591 0.01536 0.00845 -0.0292 0.6665 0.9940
4.000 0.5828 0.01587 0.00813 -0.0276 0.4951 0.9974
4.250 0.5970 0.01752 0.00850 -0.0258 0.2577 1.0000
4.500 0.6042 0.01957 0.00939 -0.0231 0.0734 1.0000
4.750 0.6185 0.02055 0.01028 -0.0208 0.0496 1.0000
5.000 0.6326 0.02141 0.01121 -0.0185 0.0403 1.0000
5.250 0.6448 0.02236 0.01225 -0.0159 0.0347 1.0000
5.500 0.6572 0.02325 0.01329 -0.0131 0.0322 1.0000
5.750 0.6697 0.02417 0.01432 -0.0105 0.0292 1.0000
6.000 0.6819 0.02517 0.01534 -0.0080 0.0262 1.0000
6.250 0.6949 0.02674 0.01691 -0.0055 0.0246 1.0000
6.500 0.7128 0.02813 0.01846 -0.0036 0.0237 1.0000
6.750 0.7322 0.02978 0.02032 -0.0019 0.0228 1.0000
7.000 0.7504 0.03146 0.02227 0.0000 0.0214 1.0000
7.250 0.7664 0.03322 0.02433 0.0022 0.0198 1.0000
7.500 0.7804 0.03533 0.02683 0.0047 0.0191 1.0000
7.750 0.7915 0.03768 0.02954 0.0076 0.0187 1.0000
8.000 0.7990 0.04018 0.03240 0.0109 0.0185 1.0000
8.250 0.8031 0.04280 0.03539 0.0146 0.0184 1.0000
8.500 0.8038 0.04554 0.03849 0.0186 0.0184 1.0000
8.750 0.8013 0.04838 0.04166 0.0227 0.0184 1.0000
9.000 0.7956 0.05127 0.04485 0.0270 0.0185 1.0000
9.250 0.7871 0.05416 0.04802 0.0312 0.0185 1.0000
9.500 0.7758 0.05708 0.05117 0.0352 0.0185 1.0000
9.750 0.7603 0.05985 0.05413 0.0394 0.0185 1.0000
10.000 0.7423 0.06278 0.05723 0.0430 0.0185 1.0000
10.250 0.7234 0.06625 0.06087 0.0451 0.0187 1.0000
10.500 0.7035 0.07036 0.06512 0.0457 0.0188 1.0000
10.750 0.6825 0.07538 0.07027 0.0445 0.0191 1.0000
11.000 0.6613 0.08158 0.07658 0.0412 0.0195 1.0000
11.250 0.6418 0.08931 0.08438 0.0360 0.0199 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0012-34 (naca001234-il)