NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M27 AIRFOIL (m27-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.16 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m27-il-1000000-n5.txt Download as CSV file: xf-m27-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M27 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2082 0.09772 0.09452 -0.0130 0.5233 0.0104
-8.250 -0.2025 0.09451 0.09130 -0.0150 0.5209 0.0107
-8.000 -0.2068 0.08914 0.08595 -0.0189 0.5193 0.0117
-7.750 -0.1997 0.08701 0.08382 -0.0203 0.5166 0.0118
-7.500 -0.1874 0.08471 0.08150 -0.0224 0.5136 0.0119
-7.250 -0.1743 0.08229 0.07906 -0.0246 0.5108 0.0121
-7.000 -0.1608 0.07957 0.07630 -0.0270 0.5081 0.0123
-6.750 -0.1464 0.07669 0.07339 -0.0295 0.5056 0.0126
-6.500 -0.1311 0.07359 0.07027 -0.0321 0.5036 0.0129
-6.250 -0.1170 0.06770 0.06431 -0.0367 0.5018 0.0143
-6.000 -0.0980 0.06573 0.06230 -0.0383 0.4988 0.0144
-5.750 -0.0781 0.06361 0.06014 -0.0399 0.4956 0.0146
-5.500 -0.0576 0.06138 0.05785 -0.0417 0.4925 0.0148
-5.250 -0.0364 0.05893 0.05534 -0.0435 0.4897 0.0151
-5.000 -0.0145 0.05634 0.05270 -0.0452 0.4878 0.0154
-4.750 0.0081 0.05364 0.04993 -0.0469 0.4855 0.0157
-4.500 0.0341 0.04821 0.04433 -0.0496 0.4835 0.0172
-4.250 0.0569 0.04630 0.04236 -0.0505 0.4805 0.0174
-4.000 0.0805 0.04473 0.04072 -0.0513 0.4773 0.0176
-3.500 0.1298 0.04115 0.03700 -0.0528 0.4721 0.0180
-3.250 0.1551 0.03916 0.03493 -0.0534 0.4698 0.0182
-3.000 0.1809 0.03717 0.03285 -0.0540 0.4673 0.0185
-2.750 0.2070 0.03521 0.03078 -0.0544 0.4646 0.0192
-2.500 0.2335 0.03287 0.02831 -0.0546 0.4619 0.0195
-2.250 0.2604 0.03035 0.02561 -0.0546 0.4591 0.0199
-2.000 0.2871 0.02772 0.02280 -0.0544 0.4569 0.0202
-1.750 0.3142 0.02469 0.01956 -0.0538 0.4547 0.0206
-1.500 0.3394 0.02168 0.01631 -0.0531 0.4524 0.0209
-1.250 0.3663 0.02019 0.01468 -0.0529 0.4499 0.0212
-0.750 0.4181 0.01352 0.00715 -0.0512 0.4451 0.0222
-0.500 0.4465 0.01274 0.00618 -0.0513 0.4423 0.0225
-0.250 0.4752 0.01223 0.00556 -0.0515 0.4399 0.0227
0.000 0.5040 0.01187 0.00512 -0.0518 0.4372 0.0231
0.250 0.5327 0.01152 0.00468 -0.0520 0.4345 0.0234
0.500 0.5612 0.01122 0.00431 -0.0523 0.4318 0.0236
0.750 0.5896 0.01101 0.00403 -0.0525 0.4290 0.0239
1.000 0.6179 0.01084 0.00381 -0.0527 0.4264 0.0242
1.250 0.6462 0.01069 0.00365 -0.0529 0.4240 0.0245
1.500 0.6745 0.01059 0.00352 -0.0531 0.4213 0.0247
1.750 0.7023 0.01045 0.00336 -0.0532 0.4186 0.0250
2.000 0.7296 0.01029 0.00318 -0.0533 0.4160 0.0255
2.250 0.7571 0.01023 0.00311 -0.0534 0.4133 0.0259
2.500 0.7848 0.01019 0.00307 -0.0536 0.4108 0.0264
2.750 0.8127 0.01015 0.00304 -0.0538 0.4085 0.0268
3.000 0.8405 0.01013 0.00303 -0.0540 0.4058 0.0274
3.250 0.8683 0.01014 0.00304 -0.0542 0.4031 0.0284
3.500 0.8961 0.01016 0.00306 -0.0545 0.4005 0.0291
3.750 0.9237 0.01021 0.00309 -0.0547 0.3979 0.0297
4.000 0.9514 0.01024 0.00313 -0.0550 0.3955 0.0306
4.250 0.9792 0.01026 0.00317 -0.0553 0.3933 0.0322
4.500 1.0070 0.01030 0.00323 -0.0556 0.3906 0.0342
4.750 1.0347 0.01036 0.00330 -0.0558 0.3879 0.0391
5.000 1.0619 0.01041 0.00344 -0.0561 0.3853 0.0746
5.250 1.0892 0.01051 0.00356 -0.0564 0.3827 0.0903
5.500 1.1166 0.01060 0.00369 -0.0567 0.3805 0.1051
5.750 1.1441 0.01065 0.00382 -0.0570 0.3784 0.1370
6.000 1.1710 0.01067 0.00399 -0.0573 0.3759 0.2229
6.250 1.1803 0.00946 0.00426 -0.0537 0.3736 0.9535
6.500 1.2122 0.00971 0.00452 -0.0550 0.3692 0.9743
6.750 1.2433 0.00996 0.00475 -0.0562 0.3632 0.9817
7.000 1.2804 0.01020 0.00498 -0.0588 0.3576 0.9854
7.500 1.3562 0.01075 0.00550 -0.0647 0.3453 0.9894
7.750 1.3891 0.01113 0.00583 -0.0666 0.3358 0.9917
8.000 1.4174 0.01139 0.00608 -0.0674 0.3278 0.9932
8.250 1.4422 0.01178 0.00641 -0.0677 0.3171 0.9939
8.500 1.4668 0.01240 0.00692 -0.0683 0.2959 0.9944
8.750 1.4881 0.01333 0.00769 -0.0686 0.2679 0.9952
9.000 1.4927 0.01578 0.00972 -0.0677 0.2052 0.9973
9.250 1.4642 0.01913 0.01285 -0.0627 0.1587 1.0000
9.500 1.4362 0.02164 0.01532 -0.0565 0.1401 1.0000
9.750 1.4073 0.02511 0.01869 -0.0517 0.1139 1.0000
10.000 1.3798 0.02913 0.02262 -0.0481 0.0854 1.0000
10.250 1.3544 0.03345 0.02688 -0.0454 0.0575 1.0000
10.500 1.3299 0.03799 0.03137 -0.0432 0.0283 1.0000
10.750 1.3224 0.04111 0.03449 -0.0420 0.0179 1.0000
11.000 1.3239 0.04346 0.03689 -0.0413 0.0159 1.0000
11.250 1.3258 0.04584 0.03931 -0.0407 0.0146 1.0000
11.500 1.3272 0.04835 0.04187 -0.0402 0.0135 1.0000
11.750 1.3301 0.05074 0.04432 -0.0398 0.0129 1.0000
12.000 1.3334 0.05309 0.04672 -0.0394 0.0124 1.0000
12.250 1.3350 0.05569 0.04937 -0.0390 0.0119 1.0000
12.500 1.3367 0.05831 0.05204 -0.0387 0.0114 1.0000
12.750 1.3375 0.06105 0.05483 -0.0385 0.0109 1.0000
13.000 1.3369 0.06398 0.05781 -0.0382 0.0105 1.0000
13.250 1.3376 0.06679 0.06067 -0.0380 0.0101 1.0000
13.500 1.3389 0.06959 0.06353 -0.0379 0.0098 1.0000
13.750 1.3410 0.07226 0.06626 -0.0378 0.0095 1.0000
14.000 1.3414 0.07518 0.06923 -0.0377 0.0092 1.0000
14.250 1.3429 0.07798 0.07208 -0.0377 0.0089 1.0000
14.500 1.3431 0.08099 0.07515 -0.0377 0.0086 1.0000
14.750 1.3435 0.08399 0.07819 -0.0378 0.0083 1.0000
15.000 1.3430 0.08710 0.08136 -0.0379 0.0080 1.0000
15.250 1.3411 0.09042 0.08473 -0.0380 0.0078 1.0000
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Polar data table (+)
Polar graphs
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