NACA 0010-35 (naca001035-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NACA 0010-35 (naca001035-il) Reynolds number: 100,000 Max Cl/Cd: 27.13 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001035-il-100000-n5.txt Download as CSV file: xf-naca001035-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4781 0.09346 0.08872 -0.0380 1.0000 0.0211
-10.250 -0.4855 0.08885 0.08415 -0.0389 1.0000 0.0207
-10.000 -0.4952 0.08377 0.07911 -0.0404 1.0000 0.0203
-9.750 -0.5081 0.07808 0.07344 -0.0429 1.0000 0.0201
-9.250 -0.6367 0.07904 0.07399 -0.0413 1.0000 0.0210
-9.000 -0.6541 0.07618 0.07111 -0.0384 1.0000 0.0207
-8.750 -0.6730 0.07373 0.06863 -0.0342 1.0000 0.0205
-8.500 -0.6883 0.07093 0.06577 -0.0302 1.0000 0.0202
-8.250 -0.7015 0.06803 0.06279 -0.0262 1.0000 0.0198
-8.000 -0.7127 0.06504 0.05968 -0.0221 1.0000 0.0194
-7.750 -0.7217 0.06199 0.05648 -0.0179 1.0000 0.0190
-7.500 -0.7285 0.05887 0.05318 -0.0137 1.0000 0.0186
-7.250 -0.7331 0.05570 0.04979 -0.0094 1.0000 0.0182
-7.000 -0.7353 0.05250 0.04634 -0.0052 1.0000 0.0177
-6.750 -0.7352 0.04930 0.04284 -0.0010 1.0000 0.0173
-6.500 -0.7326 0.04611 0.03933 0.0032 1.0000 0.0170
-6.250 -0.7275 0.04299 0.03583 0.0071 1.0000 0.0167
-6.000 -0.7194 0.04002 0.03247 0.0108 1.0000 0.0166
-5.750 -0.7085 0.03743 0.02947 0.0141 1.0000 0.0173
-5.500 -0.6948 0.03501 0.02661 0.0170 1.0000 0.0184
-5.250 -0.6781 0.03260 0.02374 0.0196 1.0000 0.0192
-5.000 -0.6582 0.03020 0.02090 0.0218 1.0000 0.0195
-4.750 -0.6351 0.02801 0.01826 0.0233 1.0000 0.0200
-4.500 -0.6103 0.02612 0.01604 0.0245 1.0000 0.0208
-4.250 -0.5868 0.02444 0.01418 0.0255 1.0000 0.0232
-4.000 -0.5665 0.02314 0.01284 0.0269 1.0000 0.0263
-3.750 -0.5477 0.02195 0.01153 0.0288 1.0000 0.0289
-3.500 -0.5305 0.02096 0.01041 0.0308 1.0000 0.0337
-3.250 -0.5127 0.02015 0.00948 0.0328 1.0000 0.0410
-3.000 -0.4948 0.01926 0.00854 0.0346 1.0000 0.0573
-2.750 -0.4789 0.01766 0.00773 0.0365 1.0000 0.1956
-2.500 -0.3079 0.01938 0.01180 0.0143 1.0000 0.9494
-2.250 -0.2746 0.01938 0.01156 0.0126 1.0000 0.9572
-2.000 -0.2412 0.01936 0.01134 0.0108 1.0000 0.9644
-1.750 -0.2049 0.01933 0.01111 0.0084 1.0000 0.9706
-1.500 -0.1714 0.01933 0.01096 0.0065 1.0000 0.9778
-1.250 -0.1355 0.01925 0.01075 0.0040 1.0000 0.9827
-1.000 -0.1032 0.01921 0.01062 0.0021 1.0000 0.9880
-0.750 -0.0700 0.01915 0.01050 0.0001 1.0000 0.9925
-0.500 -0.0372 0.01912 0.01041 -0.0019 1.0000 0.9969
-0.250 -0.0101 0.01909 0.01037 -0.0027 1.0000 1.0000
0.000 0.0000 0.01908 0.01035 0.0000 1.0000 1.0000
0.250 0.0101 0.01909 0.01037 0.0027 1.0000 1.0000
0.500 0.0372 0.01911 0.01041 0.0019 0.9969 1.0000
0.750 0.0699 0.01915 0.01050 -0.0001 0.9926 1.0000
1.000 0.1031 0.01921 0.01062 -0.0021 0.9880 1.0000
1.250 0.1355 0.01925 0.01075 -0.0039 0.9827 1.0000
1.500 0.1713 0.01932 0.01095 -0.0064 0.9779 1.0000
1.750 0.2048 0.01933 0.01110 -0.0084 0.9706 1.0000
2.000 0.2412 0.01936 0.01134 -0.0108 0.9645 1.0000
2.250 0.2746 0.01937 0.01156 -0.0126 0.9572 1.0000
2.500 0.3079 0.01937 0.01180 -0.0143 0.9494 1.0000
2.750 0.4788 0.01765 0.00773 -0.0365 0.1959 1.0000
3.000 0.4947 0.01925 0.00854 -0.0346 0.0574 1.0000
3.250 0.5126 0.02015 0.00947 -0.0327 0.0410 1.0000
3.500 0.5304 0.02096 0.01041 -0.0308 0.0337 1.0000
3.750 0.5476 0.02195 0.01153 -0.0288 0.0289 1.0000
4.000 0.5664 0.02313 0.01283 -0.0269 0.0263 1.0000
4.250 0.5867 0.02444 0.01418 -0.0255 0.0232 1.0000
4.500 0.6102 0.02612 0.01604 -0.0245 0.0208 1.0000
4.750 0.6350 0.02801 0.01826 -0.0233 0.0200 1.0000
5.000 0.6581 0.03020 0.02089 -0.0217 0.0195 1.0000
5.250 0.6780 0.03259 0.02374 -0.0196 0.0192 1.0000
5.500 0.6948 0.03500 0.02660 -0.0170 0.0184 1.0000
5.750 0.7085 0.03742 0.02945 -0.0141 0.0173 1.0000
6.000 0.7194 0.04002 0.03246 -0.0108 0.0166 1.0000
6.250 0.7274 0.04298 0.03582 -0.0071 0.0167 1.0000
6.500 0.7326 0.04611 0.03932 -0.0032 0.0170 1.0000
6.750 0.7352 0.04929 0.04283 0.0010 0.0173 1.0000
7.000 0.7353 0.05250 0.04633 0.0052 0.0177 1.0000
7.250 0.7331 0.05569 0.04978 0.0095 0.0182 1.0000
7.500 0.7285 0.05887 0.05317 0.0137 0.0186 1.0000
7.750 0.7217 0.06199 0.05648 0.0180 0.0190 1.0000
8.000 0.7127 0.06504 0.05968 0.0221 0.0194 1.0000
8.250 0.7016 0.06802 0.06278 0.0262 0.0198 1.0000
8.500 0.6885 0.07092 0.06577 0.0302 0.0202 1.0000
8.750 0.6732 0.07373 0.06863 0.0341 0.0205 1.0000
9.000 0.6543 0.07619 0.07112 0.0383 0.0207 1.0000
9.250 0.6370 0.07905 0.07400 0.0413 0.0210 1.0000
9.500 0.5249 0.07259 0.06794 0.0448 0.0199 1.0000
9.750 0.5077 0.07792 0.07328 0.0429 0.0201 1.0000
10.000 0.4948 0.08361 0.07894 0.0404 0.0203 1.0000
10.250 0.4851 0.08870 0.08400 0.0389 0.0207 1.0000
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Polar data table (+)
Polar graphs
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