NACA M12 AIRFOIL (m12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 AIRFOIL (m12-il) Reynolds number: 200,000 Max Cl/Cd: 62.44 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m12-il-200000-n5.txt Download as CSV file: xf-m12-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6567 0.07418 0.07034 -0.0372 1.0000 0.0306
-10.750 -0.7311 0.05674 0.05256 -0.0505 1.0000 0.0302
-10.500 -0.7677 0.05124 0.04677 -0.0486 1.0000 0.0303
-10.250 -0.7940 0.04600 0.04107 -0.0457 1.0000 0.0306
-10.000 -0.8083 0.04172 0.03625 -0.0426 1.0000 0.0311
-9.750 -0.8081 0.03878 0.03300 -0.0402 1.0000 0.0315
-9.500 -0.7982 0.03699 0.03110 -0.0384 1.0000 0.0320
-9.250 -0.7873 0.03540 0.02937 -0.0366 1.0000 0.0325
-9.000 -0.7767 0.03376 0.02754 -0.0345 1.0000 0.0329
-8.750 -0.7658 0.03215 0.02573 -0.0323 1.0000 0.0333
-8.500 -0.7539 0.03066 0.02405 -0.0301 1.0000 0.0338
-8.250 -0.7414 0.02938 0.02259 -0.0279 1.0000 0.0344
-8.000 -0.7288 0.02817 0.02119 -0.0256 1.0000 0.0351
-7.750 -0.7111 0.02687 0.01965 -0.0242 0.9988 0.0359
-7.500 -0.6800 0.02533 0.01781 -0.0256 0.9946 0.0365
-7.250 -0.6487 0.02399 0.01622 -0.0267 0.9896 0.0371
-7.000 -0.6157 0.02284 0.01485 -0.0282 0.9852 0.0376
-6.750 -0.5837 0.02158 0.01346 -0.0295 0.9801 0.0382
-6.500 -0.5510 0.02057 0.01243 -0.0309 0.9747 0.0392
-6.250 -0.5190 0.01979 0.01161 -0.0321 0.9683 0.0403
-6.000 -0.4867 0.01901 0.01077 -0.0332 0.9615 0.0412
-5.750 -0.4558 0.01827 0.00996 -0.0340 0.9535 0.0420
-5.500 -0.4238 0.01757 0.00920 -0.0350 0.9462 0.0429
-5.250 -0.3945 0.01695 0.00852 -0.0353 0.9368 0.0438
-5.000 -0.3633 0.01637 0.00787 -0.0360 0.9290 0.0448
-4.750 -0.3362 0.01584 0.00730 -0.0359 0.9180 0.0458
-4.500 -0.3086 0.01532 0.00678 -0.0359 0.9081 0.0477
-4.250 -0.2810 0.01492 0.00635 -0.0358 0.8979 0.0499
-4.000 -0.2547 0.01456 0.00595 -0.0354 0.8865 0.0522
-3.750 -0.2284 0.01420 0.00554 -0.0350 0.8757 0.0548
-3.500 -0.2024 0.01385 0.00518 -0.0345 0.8649 0.0592
-3.250 -0.1767 0.01354 0.00486 -0.0339 0.8531 0.0663
-3.000 -0.1511 0.01321 0.00456 -0.0334 0.8419 0.0806
-2.750 -0.1254 0.01289 0.00432 -0.0329 0.8311 0.1049
-2.500 -0.0999 0.01260 0.00411 -0.0324 0.8194 0.1353
-2.250 -0.0744 0.01231 0.00391 -0.0319 0.8081 0.1671
-2.000 -0.0493 0.01197 0.00371 -0.0314 0.7971 0.2120
-1.750 -0.0261 0.01142 0.00353 -0.0307 0.7858 0.3110
-1.500 -0.0056 0.01067 0.00336 -0.0294 0.7743 0.4591
-1.250 0.0105 0.00978 0.00335 -0.0267 0.7637 0.6770
-1.000 0.0354 0.00956 0.00355 -0.0250 0.7529 0.8074
-0.750 0.0661 0.00964 0.00367 -0.0249 0.7415 0.8613
-0.500 0.0975 0.00976 0.00374 -0.0250 0.7306 0.8910
-0.250 0.1302 0.00993 0.00382 -0.0255 0.7194 0.9165
0.000 0.1657 0.01011 0.00394 -0.0265 0.7074 0.9371
0.250 0.2047 0.01031 0.00405 -0.0284 0.6956 0.9529
0.500 0.2517 0.01052 0.00415 -0.0321 0.6833 0.9659
0.750 0.2928 0.01064 0.00417 -0.0348 0.6706 0.9748
1.000 0.3288 0.01068 0.00414 -0.0366 0.6572 0.9797
1.250 0.3616 0.01073 0.00411 -0.0377 0.6436 0.9843
1.500 0.3970 0.01077 0.00407 -0.0394 0.6290 0.9875
1.750 0.4309 0.01082 0.00404 -0.0408 0.6128 0.9913
2.000 0.4645 0.01089 0.00403 -0.0421 0.5963 0.9948
2.250 0.4990 0.01095 0.00402 -0.0437 0.5812 0.9978
2.500 0.5303 0.01103 0.00404 -0.0446 0.5674 1.0000
2.750 0.5546 0.01111 0.00406 -0.0440 0.5546 1.0000
3.250 0.6026 0.01130 0.00418 -0.0427 0.5292 1.0000
3.500 0.6265 0.01141 0.00426 -0.0420 0.5165 1.0000
3.750 0.6501 0.01154 0.00436 -0.0412 0.5043 1.0000
4.000 0.6735 0.01168 0.00448 -0.0404 0.4918 1.0000
4.250 0.6967 0.01184 0.00461 -0.0396 0.4786 1.0000
4.500 0.7198 0.01199 0.00475 -0.0388 0.4650 1.0000
4.750 0.7424 0.01218 0.00491 -0.0378 0.4491 1.0000
5.000 0.7642 0.01240 0.00507 -0.0367 0.4293 1.0000
5.250 0.7859 0.01263 0.00526 -0.0356 0.4071 1.0000
5.500 0.8065 0.01292 0.00545 -0.0343 0.3820 1.0000
5.750 0.8267 0.01324 0.00568 -0.0330 0.3529 1.0000
6.000 0.8466 0.01360 0.00593 -0.0317 0.3241 1.0000
6.250 0.8662 0.01399 0.00623 -0.0303 0.2971 1.0000
6.500 0.8853 0.01443 0.00657 -0.0289 0.2715 1.0000
6.750 0.9041 0.01490 0.00694 -0.0274 0.2462 1.0000
7.000 0.9226 0.01539 0.00734 -0.0259 0.2227 1.0000
7.250 0.9408 0.01590 0.00778 -0.0244 0.2000 1.0000
7.500 0.9587 0.01646 0.00826 -0.0229 0.1752 1.0000
7.750 0.9754 0.01712 0.00879 -0.0212 0.1471 1.0000
8.000 0.9912 0.01786 0.00938 -0.0195 0.1206 1.0000
8.250 1.0069 0.01862 0.01004 -0.0177 0.1007 1.0000
8.500 1.0229 0.01935 0.01071 -0.0160 0.0872 1.0000
8.750 1.0392 0.02005 0.01142 -0.0144 0.0774 1.0000
9.000 1.0547 0.02079 0.01216 -0.0127 0.0703 1.0000
9.250 1.0698 0.02153 0.01292 -0.0110 0.0644 1.0000
9.500 1.0839 0.02231 0.01373 -0.0091 0.0603 1.0000
9.750 1.0980 0.02305 0.01455 -0.0073 0.0566 1.0000
10.000 1.1082 0.02390 0.01542 -0.0049 0.0536 1.0000
10.250 1.1174 0.02481 0.01637 -0.0025 0.0511 1.0000
10.500 1.1285 0.02567 0.01733 -0.0005 0.0488 1.0000
10.750 1.1388 0.02665 0.01837 0.0014 0.0466 1.0000
11.000 1.1469 0.02782 0.01958 0.0032 0.0446 1.0000
11.250 1.1540 0.02915 0.02097 0.0050 0.0430 1.0000
11.500 1.1642 0.03032 0.02227 0.0064 0.0413 1.0000
11.750 1.1733 0.03163 0.02367 0.0077 0.0396 1.0000
12.000 1.1812 0.03308 0.02519 0.0088 0.0381 1.0000
12.250 1.1863 0.03482 0.02698 0.0100 0.0368 1.0000
12.500 1.1918 0.03663 0.02887 0.0110 0.0356 1.0000
12.750 1.1994 0.03831 0.03070 0.0117 0.0342 1.0000
13.000 1.2056 0.04016 0.03266 0.0124 0.0329 1.0000
13.250 1.2108 0.04216 0.03475 0.0128 0.0318 1.0000
13.500 1.2143 0.04437 0.03704 0.0132 0.0308 1.0000
13.750 1.2150 0.04691 0.03962 0.0135 0.0300 1.0000
14.000 1.2191 0.04923 0.04210 0.0137 0.0291 1.0000
14.250 1.2220 0.05171 0.04473 0.0138 0.0281 1.0000
14.500 1.2237 0.05437 0.04753 0.0137 0.0271 1.0000
14.750 1.2244 0.05719 0.05046 0.0133 0.0263 1.0000
15.000 1.2241 0.06021 0.05357 0.0128 0.0257 1.0000
15.250 1.2226 0.06343 0.05687 0.0122 0.0251 1.0000
15.500 1.2201 0.06682 0.06032 0.0116 0.0246 1.0000
15.750 1.2180 0.07038 0.06408 0.0108 0.0240 1.0000
16.000 1.2145 0.07418 0.06806 0.0098 0.0234 1.0000
16.250 1.2102 0.07822 0.07226 0.0085 0.0228 1.0000
16.500 1.2052 0.08246 0.07665 0.0070 0.0223 1.0000
16.750 1.1996 0.08691 0.08123 0.0052 0.0218 1.0000
17.000 1.1934 0.09153 0.08597 0.0033 0.0214 1.0000
17.250 1.1869 0.09633 0.09089 0.0012 0.0210 1.0000
17.500 1.1801 0.10125 0.09591 -0.0011 0.0207 1.0000
17.750 1.1731 0.10626 0.10101 -0.0035 0.0204 1.0000
18.000 1.1653 0.11144 0.10627 -0.0059 0.0201 1.0000
18.250 1.1518 0.11804 0.11308 -0.0093 0.0198 1.0000
18.500 1.1368 0.12516 0.12041 -0.0131 0.0196 1.0000
18.750 1.1198 0.13295 0.12840 -0.0175 0.0194 1.0000
19.000 1.0997 0.14176 0.13740 -0.0226 0.0193 1.0000
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