NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.13 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651212a06-il-1000000.txt Download as CSV file: xf-naca651212a06-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212 a=0.6
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5460 0.08259 0.08104 -0.0385 1.0000 0.0143
-10.500 -0.7796 0.03908 0.03646 -0.0547 0.9252 0.0102
-10.250 -0.8005 0.03423 0.03119 -0.0504 0.9061 0.0105
-10.000 -0.7956 0.03221 0.02893 -0.0482 0.8943 0.0109
-9.750 -0.7974 0.02843 0.02470 -0.0452 0.8833 0.0114
-9.500 -0.7908 0.02535 0.02122 -0.0430 0.8739 0.0117
-9.250 -0.7744 0.02393 0.01955 -0.0417 0.8662 0.0120
-9.000 -0.7553 0.02289 0.01831 -0.0407 0.8586 0.0123
-8.750 -0.7447 0.01938 0.01436 -0.0388 0.8518 0.0128
-8.500 -0.7226 0.01863 0.01354 -0.0383 0.8453 0.0132
-8.250 -0.6994 0.01823 0.01305 -0.0378 0.8392 0.0136
-8.000 -0.6757 0.01761 0.01234 -0.0374 0.8332 0.0140
-7.750 -0.6516 0.01711 0.01175 -0.0371 0.8273 0.0145
-7.500 -0.6273 0.01656 0.01110 -0.0367 0.8221 0.0151
-7.250 -0.6027 0.01586 0.01030 -0.0363 0.8167 0.0156
-7.000 -0.5780 0.01529 0.00962 -0.0359 0.8114 0.0160
-6.750 -0.5526 0.01486 0.00910 -0.0356 0.8065 0.0162
-6.500 -0.5322 0.01321 0.00734 -0.0347 0.8014 0.0171
-6.250 -0.5078 0.01267 0.00676 -0.0343 0.7966 0.0177
-6.000 -0.4822 0.01235 0.00640 -0.0341 0.7922 0.0184
-5.750 -0.4561 0.01202 0.00605 -0.0339 0.7877 0.0193
-5.500 -0.4305 0.01164 0.00562 -0.0337 0.7831 0.0200
-5.250 -0.4051 0.01127 0.00518 -0.0334 0.7787 0.0206
-5.000 -0.3787 0.01098 0.00485 -0.0332 0.7745 0.0211
-4.750 -0.3546 0.01033 0.00413 -0.0327 0.7702 0.0222
-4.500 -0.3292 0.00991 0.00366 -0.0324 0.7662 0.0236
-4.250 -0.3026 0.00970 0.00342 -0.0323 0.7623 0.0250
-4.000 -0.2754 0.00947 0.00317 -0.0323 0.7584 0.0266
-3.750 -0.2481 0.00928 0.00295 -0.0323 0.7543 0.0277
-3.500 -0.2218 0.00895 0.00256 -0.0321 0.7505 0.0305
-3.250 -0.1946 0.00875 0.00234 -0.0321 0.7469 0.0340
-3.000 -0.1669 0.00858 0.00216 -0.0322 0.7434 0.0373
-2.750 -0.1400 0.00830 0.00195 -0.0322 0.7396 0.0551
-2.500 -0.1167 0.00751 0.00167 -0.0318 0.7358 0.1974
-2.250 -0.0956 0.00646 0.00137 -0.0312 0.7322 0.4154
-2.000 -0.0713 0.00590 0.00129 -0.0308 0.7288 0.5518
-1.750 -0.0439 0.00577 0.00127 -0.0308 0.7252 0.5908
-1.500 -0.0160 0.00571 0.00124 -0.0309 0.7217 0.6151
-1.250 0.0117 0.00567 0.00123 -0.0309 0.7181 0.6397
-1.000 0.0395 0.00561 0.00124 -0.0309 0.7149 0.6636
-0.750 0.0675 0.00557 0.00126 -0.0310 0.7113 0.6849
-0.500 0.0956 0.00554 0.00126 -0.0310 0.7078 0.7002
-0.250 0.1237 0.00554 0.00126 -0.0311 0.7044 0.7106
0.000 0.1523 0.00556 0.00126 -0.0314 0.7011 0.7178
0.250 0.1808 0.00553 0.00128 -0.0316 0.6976 0.7247
0.500 0.2095 0.00554 0.00130 -0.0318 0.6942 0.7322
0.750 0.2379 0.00556 0.00132 -0.0320 0.6907 0.7392
1.000 0.2665 0.00562 0.00136 -0.0322 0.6872 0.7470
1.250 0.2951 0.00562 0.00141 -0.0324 0.6838 0.7536
1.500 0.3239 0.00564 0.00144 -0.0327 0.6797 0.7610
1.750 0.3522 0.00567 0.00147 -0.0329 0.6748 0.7670
2.000 0.3807 0.00569 0.00151 -0.0330 0.6688 0.7734
2.250 0.4086 0.00571 0.00149 -0.0331 0.6579 0.7793
2.500 0.4364 0.00568 0.00148 -0.0331 0.6451 0.7850
2.750 0.4644 0.00571 0.00150 -0.0332 0.6312 0.7908
3.000 0.4914 0.00571 0.00149 -0.0331 0.6120 0.7966
3.250 0.5188 0.00575 0.00152 -0.0331 0.5922 0.8028
3.500 0.5451 0.00583 0.00156 -0.0329 0.5641 0.8095
3.750 0.5695 0.00605 0.00166 -0.0324 0.5126 0.8173
4.000 0.5862 0.00685 0.00206 -0.0307 0.3867 0.8300
4.250 0.5973 0.00806 0.00283 -0.0278 0.2532 0.8467
4.500 0.6154 0.00924 0.00339 -0.0268 0.1264 0.8944
4.750 0.6333 0.01009 0.00388 -0.0254 0.0494 0.9016
5.000 0.6563 0.01048 0.00420 -0.0247 0.0349 0.9064
5.250 0.6784 0.01084 0.00455 -0.0237 0.0287 0.9115
5.500 0.7022 0.01111 0.00484 -0.0231 0.0263 0.9157
5.750 0.7245 0.01135 0.00512 -0.0222 0.0240 0.9199
6.000 0.7434 0.01188 0.00570 -0.0207 0.0212 0.9243
6.250 0.7660 0.01216 0.00600 -0.0199 0.0206 0.9278
6.500 0.7879 0.01242 0.00629 -0.0189 0.0196 0.9313
6.750 0.8090 0.01269 0.00661 -0.0179 0.0186 0.9349
7.000 0.8296 0.01302 0.00696 -0.0168 0.0177 0.9384
7.250 0.8471 0.01356 0.00752 -0.0152 0.0168 0.9414
7.500 0.8576 0.01453 0.00859 -0.0125 0.0160 0.9455
7.750 0.8769 0.01489 0.00900 -0.0112 0.0157 0.9487
8.000 0.8951 0.01528 0.00945 -0.0097 0.0154 0.9517
8.250 0.9097 0.01579 0.01001 -0.0077 0.0151 0.9548
8.500 0.9242 0.01644 0.01073 -0.0057 0.0148 0.9587
8.750 0.9426 0.01699 0.01134 -0.0046 0.0144 0.9631
9.000 0.9628 0.01774 0.01216 -0.0040 0.0140 0.9675
9.250 0.9867 0.01845 0.01293 -0.0043 0.0136 0.9725
9.500 1.0139 0.01902 0.01352 -0.0052 0.0130 0.9800
9.750 1.0324 0.01993 0.01446 -0.0046 0.0126 1.0000
10.000 1.0457 0.02118 0.01578 -0.0030 0.0123 1.0000
10.250 1.0626 0.02344 0.01820 -0.0019 0.0119 1.0000
10.500 1.0781 0.02424 0.01909 -0.0006 0.0118 1.0000
10.750 1.0929 0.02507 0.02002 0.0008 0.0116 1.0000
11.000 1.1076 0.02626 0.02132 0.0020 0.0115 1.0000
11.250 1.1210 0.02763 0.02282 0.0034 0.0114 1.0000
11.500 1.1327 0.02896 0.02428 0.0049 0.0111 1.0000
11.750 1.1431 0.03010 0.02553 0.0063 0.0109 1.0000
12.000 1.1512 0.03172 0.02730 0.0079 0.0107 1.0000
12.250 1.1587 0.03309 0.02880 0.0094 0.0105 1.0000
12.500 1.1665 0.03414 0.02991 0.0108 0.0101 1.0000
12.750 1.1713 0.03580 0.03169 0.0122 0.0100 1.0000
13.000 1.1741 0.03769 0.03371 0.0136 0.0099 1.0000
13.250 1.1765 0.03948 0.03561 0.0148 0.0097 1.0000
13.500 1.1807 0.04096 0.03716 0.0156 0.0096 1.0000
13.750 1.1801 0.04323 0.03956 0.0166 0.0095 1.0000
14.000 1.1771 0.04582 0.04227 0.0174 0.0094 1.0000
14.250 1.1668 0.04949 0.04614 0.0181 0.0094 1.0000
14.500 1.1655 0.05188 0.04858 0.0182 0.0091 1.0000
14.750 1.1503 0.05633 0.05322 0.0181 0.0091 1.0000
15.000 1.1341 0.06112 0.05819 0.0174 0.0090 1.0000
15.250 1.1160 0.06666 0.06394 0.0161 0.0091 1.0000
15.500 1.0969 0.07264 0.07008 0.0139 0.0090 1.0000
15.750 1.0693 0.08068 0.07832 0.0102 0.0090 1.0000
16.000 1.0554 0.08717 0.08495 0.0067 0.0091 1.0000
16.250 1.0238 0.09786 0.09583 0.0003 0.0090 1.0000
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Polar data table (+)
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