NACA M12 AIRFOIL (m12-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M12 AIRFOIL (m12-il) Reynolds number: 500,000 Max Cl/Cd: 86.74 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m12-il-500000.txt Download as CSV file: xf-m12-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5596 0.09890 0.09650 -0.0191 1.0000 0.0373
-10.500 -0.8014 0.04841 0.04506 -0.0466 1.0000 0.0304
-10.250 -0.8154 0.04407 0.04042 -0.0439 1.0000 0.0304
-10.000 -0.8243 0.03980 0.03584 -0.0410 1.0000 0.0305
-9.750 -0.8255 0.03632 0.03208 -0.0383 1.0000 0.0307
-9.500 -0.8203 0.03379 0.02936 -0.0358 1.0000 0.0310
-9.250 -0.8084 0.03236 0.02786 -0.0338 1.0000 0.0314
-9.000 -0.7937 0.03151 0.02700 -0.0320 1.0000 0.0318
-8.750 -0.7856 0.02989 0.02522 -0.0291 1.0000 0.0322
-8.500 -0.7767 0.02869 0.02389 -0.0262 1.0000 0.0327
-8.250 -0.7698 0.02740 0.02244 -0.0229 1.0000 0.0332
-8.000 -0.7442 0.02540 0.02016 -0.0234 0.9978 0.0338
-7.750 -0.7131 0.02342 0.01788 -0.0248 0.9952 0.0342
-7.500 -0.6806 0.02186 0.01607 -0.0262 0.9925 0.0347
-7.250 -0.6474 0.02082 0.01483 -0.0276 0.9888 0.0354
-7.000 -0.6119 0.02020 0.01403 -0.0294 0.9857 0.0359
-6.750 -0.5785 0.01798 0.01165 -0.0311 0.9836 0.0365
-6.500 -0.5453 0.01671 0.01033 -0.0325 0.9799 0.0371
-6.250 -0.5121 0.01584 0.00944 -0.0338 0.9751 0.0378
-6.000 -0.4776 0.01514 0.00870 -0.0353 0.9709 0.0386
-5.750 -0.4477 0.01457 0.00810 -0.0358 0.9628 0.0396
-5.500 -0.4165 0.01396 0.00745 -0.0365 0.9561 0.0404
-5.250 -0.3902 0.01343 0.00688 -0.0361 0.9453 0.0411
-5.000 -0.3639 0.01296 0.00636 -0.0356 0.9349 0.0417
-4.500 -0.3147 0.01204 0.00531 -0.0340 0.9122 0.0432
-4.250 -0.2908 0.01154 0.00479 -0.0331 0.9005 0.0447
-4.000 -0.2657 0.01123 0.00444 -0.0324 0.8897 0.0464
-3.750 -0.2401 0.01097 0.00414 -0.0317 0.8780 0.0481
-3.500 -0.2141 0.01073 0.00385 -0.0312 0.8665 0.0498
-3.250 -0.1885 0.01042 0.00349 -0.0306 0.8557 0.0530
-3.000 -0.1623 0.01019 0.00325 -0.0301 0.8444 0.0580
-2.750 -0.1363 0.00988 0.00299 -0.0296 0.8329 0.0733
-2.500 -0.1111 0.00948 0.00279 -0.0291 0.8220 0.1231
-2.250 -0.0853 0.00919 0.00262 -0.0287 0.8110 0.1646
-2.000 -0.0597 0.00884 0.00247 -0.0284 0.7995 0.2216
-1.750 -0.0356 0.00832 0.00232 -0.0278 0.7886 0.3320
-1.500 -0.0131 0.00770 0.00216 -0.0270 0.7778 0.4712
-1.250 0.0063 0.00692 0.00208 -0.0253 0.7663 0.6594
-1.000 0.0274 0.00651 0.00211 -0.0235 0.7555 0.7855
-0.750 0.0518 0.00645 0.00219 -0.0221 0.7448 0.8532
-0.500 0.0775 0.00649 0.00227 -0.0212 0.7332 0.8925
-0.250 0.1047 0.00658 0.00234 -0.0205 0.7220 0.9142
0.000 0.1320 0.00673 0.00242 -0.0199 0.7109 0.9330
0.250 0.1614 0.00687 0.00252 -0.0198 0.6987 0.9467
0.500 0.1943 0.00706 0.00265 -0.0205 0.6864 0.9589
0.750 0.2305 0.00728 0.00279 -0.0219 0.6733 0.9694
1.000 0.2785 0.00748 0.00289 -0.0260 0.6574 0.9729
1.250 0.3242 0.00767 0.00300 -0.0297 0.6412 0.9787
1.500 0.3688 0.00784 0.00309 -0.0332 0.6266 0.9848
1.750 0.4097 0.00793 0.00311 -0.0361 0.6121 0.9883
2.000 0.4449 0.00801 0.00311 -0.0377 0.5978 0.9914
2.250 0.4796 0.00808 0.00313 -0.0393 0.5838 0.9942
2.500 0.5162 0.00812 0.00312 -0.0414 0.5693 0.9961
2.750 0.5522 0.00818 0.00313 -0.0433 0.5552 0.9982
3.000 0.5863 0.00825 0.00316 -0.0448 0.5417 1.0000
3.250 0.6113 0.00832 0.00318 -0.0444 0.5290 1.0000
3.500 0.6363 0.00840 0.00321 -0.0439 0.5164 1.0000
3.750 0.6611 0.00848 0.00325 -0.0435 0.5030 1.0000
4.000 0.6857 0.00859 0.00330 -0.0429 0.4865 1.0000
4.250 0.7101 0.00869 0.00336 -0.0424 0.4682 1.0000
4.500 0.7341 0.00882 0.00343 -0.0418 0.4478 1.0000
4.750 0.7575 0.00899 0.00352 -0.0410 0.4251 1.0000
5.000 0.7807 0.00916 0.00363 -0.0402 0.4067 1.0000
5.250 0.8039 0.00933 0.00376 -0.0394 0.3885 1.0000
5.500 0.8266 0.00953 0.00390 -0.0385 0.3672 1.0000
6.000 0.8701 0.01006 0.00426 -0.0365 0.3185 1.0000
6.250 0.8909 0.01039 0.00449 -0.0353 0.2924 1.0000
6.500 0.9109 0.01078 0.00475 -0.0340 0.2647 1.0000
6.750 0.9305 0.01119 0.00505 -0.0326 0.2373 1.0000
7.000 0.9499 0.01162 0.00537 -0.0312 0.2113 1.0000
7.250 0.9685 0.01210 0.00572 -0.0297 0.1826 1.0000
7.500 0.9851 0.01273 0.00615 -0.0279 0.1457 1.0000
7.750 1.0001 0.01350 0.00668 -0.0258 0.1076 1.0000
8.000 1.0154 0.01424 0.00726 -0.0238 0.0825 1.0000
8.250 1.0317 0.01489 0.00782 -0.0219 0.0684 1.0000
8.500 1.0489 0.01548 0.00838 -0.0202 0.0603 1.0000
8.750 1.0677 0.01598 0.00890 -0.0188 0.0554 1.0000
9.000 1.0846 0.01662 0.00952 -0.0171 0.0511 1.0000
9.250 1.1027 0.01718 0.01013 -0.0156 0.0483 1.0000
9.500 1.1211 0.01771 0.01069 -0.0143 0.0457 1.0000
9.750 1.1365 0.01843 0.01142 -0.0125 0.0432 1.0000
10.000 1.1512 0.01917 0.01221 -0.0106 0.0412 1.0000
10.250 1.1679 0.01975 0.01285 -0.0091 0.0395 1.0000
10.500 1.1818 0.02038 0.01353 -0.0071 0.0379 1.0000
10.750 1.1908 0.02124 0.01440 -0.0045 0.0363 1.0000
11.000 1.1965 0.02238 0.01560 -0.0017 0.0349 1.0000
11.250 1.2108 0.02308 0.01638 -0.0002 0.0337 1.0000
11.500 1.2231 0.02395 0.01732 0.0015 0.0324 1.0000
11.750 1.2340 0.02495 0.01836 0.0030 0.0313 1.0000
12.000 1.2408 0.02631 0.01976 0.0048 0.0303 1.0000
12.250 1.2430 0.02813 0.02164 0.0068 0.0293 1.0000
12.500 1.2552 0.02922 0.02284 0.0077 0.0284 1.0000
12.750 1.2655 0.03051 0.02421 0.0087 0.0275 1.0000
13.000 1.2750 0.03191 0.02568 0.0095 0.0265 1.0000
13.250 1.2826 0.03351 0.02733 0.0103 0.0258 1.0000
13.500 1.2862 0.03555 0.02941 0.0112 0.0251 1.0000
13.750 1.2857 0.03803 0.03196 0.0123 0.0244 1.0000
14.000 1.2932 0.03985 0.03391 0.0126 0.0239 1.0000
14.250 1.2989 0.04189 0.03606 0.0129 0.0233 1.0000
14.500 1.3034 0.04407 0.03835 0.0132 0.0227 1.0000
14.750 1.3074 0.04637 0.04073 0.0132 0.0222 1.0000
15.000 1.3107 0.04879 0.04323 0.0131 0.0217 1.0000
15.250 1.3128 0.05136 0.04585 0.0129 0.0212 1.0000
15.500 1.3121 0.05424 0.04879 0.0128 0.0208 1.0000
15.750 1.3079 0.05751 0.05213 0.0131 0.0203 1.0000
16.000 1.3080 0.06062 0.05539 0.0123 0.0200 1.0000
16.250 1.3069 0.06394 0.05884 0.0115 0.0197 1.0000
16.500 1.3048 0.06745 0.06249 0.0106 0.0193 1.0000
16.750 1.3018 0.07118 0.06635 0.0096 0.0190 1.0000
17.000 1.2980 0.07508 0.07036 0.0083 0.0187 1.0000
17.250 1.2938 0.07913 0.07453 0.0069 0.0184 1.0000
17.500 1.2892 0.08332 0.07883 0.0054 0.0181 1.0000
17.750 1.2843 0.08762 0.08323 0.0037 0.0179 1.0000
18.000 1.2790 0.09202 0.08772 0.0019 0.0177 1.0000
18.250 1.2735 0.09651 0.09229 0.0001 0.0175 1.0000
18.500 1.2675 0.10112 0.09699 -0.0019 0.0173 1.0000
18.750 1.2602 0.10593 0.10187 -0.0039 0.0171 1.0000
19.000 1.2492 0.11130 0.10735 -0.0061 0.0168 1.0000
19.250 1.2342 0.11770 0.11391 -0.0091 0.0167 1.0000
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