DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DU 86-137/25 AIRFOIL (du861372-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.91 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-du861372-il-1000000-n5.txt Download as CSV file: xf-du861372-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DU 86-137/25 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
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7025 0.10039 0.09672 -0.0281 0.2294 0.0059
-14.250 -0.7393 0.08873 0.08493 -0.0362 0.2295 0.0057
-14.000 -0.7564 0.08262 0.07873 -0.0401 0.2294 0.0059
-13.750 -0.7866 0.07557 0.07155 -0.0438 0.2294 0.0058
-13.500 -0.8063 0.07079 0.06666 -0.0456 0.2295 0.0058
-13.250 -0.8284 0.06629 0.06203 -0.0465 0.2294 0.0058
-13.000 -0.8224 0.05622 0.05190 -0.0426 0.2296 0.0068
-12.750 -0.8414 0.05244 0.04799 -0.0418 0.2296 0.0068
-12.500 -0.8571 0.04922 0.04466 -0.0406 0.2296 0.0068
-12.250 -0.8690 0.04653 0.04187 -0.0390 0.2295 0.0068
-12.000 -0.8740 0.04444 0.03970 -0.0375 0.2294 0.0068
-11.750 -0.8870 0.04219 0.03733 -0.0349 0.2294 0.0068
-11.500 -0.8921 0.04044 0.03550 -0.0326 0.2293 0.0069
-11.250 -0.8988 0.03878 0.03376 -0.0295 0.2292 0.0069
-11.000 -0.9059 0.03714 0.03202 -0.0259 0.2290 0.0070
-10.750 -0.9044 0.03537 0.03013 -0.0236 0.2290 0.0071
-10.500 -0.9006 0.03361 0.02826 -0.0214 0.2288 0.0072
-10.250 -0.8949 0.03186 0.02638 -0.0194 0.2286 0.0073
-10.000 -0.8875 0.03009 0.02447 -0.0175 0.2285 0.0075
-9.750 -0.9007 0.03122 0.02503 -0.0106 0.2285 0.0088
-9.500 -0.8763 0.02791 0.02179 -0.0118 0.2281 0.0089
-9.250 -0.8588 0.02576 0.01956 -0.0115 0.2278 0.0090
-9.000 -0.8408 0.02399 0.01775 -0.0112 0.2277 0.0092
-8.750 -0.8235 0.02267 0.01634 -0.0104 0.2273 0.0098
-8.500 -0.8076 0.02233 0.01582 -0.0088 0.2270 0.0107
-8.250 -0.7920 0.02144 0.01470 -0.0072 0.2269 0.0108
-8.000 -0.7747 0.02030 0.01336 -0.0059 0.2266 0.0109
-7.750 -0.7568 0.01917 0.01203 -0.0047 0.2265 0.0109
-7.500 -0.7383 0.01827 0.01089 -0.0035 0.2262 0.0109
-7.250 -0.7167 0.01734 0.00980 -0.0029 0.2260 0.0110
-7.000 -0.6943 0.01651 0.00884 -0.0025 0.2258 0.0110
-6.750 -0.6711 0.01574 0.00795 -0.0022 0.2256 0.0110
-6.500 -0.6472 0.01504 0.00716 -0.0020 0.2256 0.0110
-6.250 -0.6229 0.01439 0.00643 -0.0020 0.2254 0.0110
-5.750 -0.5847 0.02557 0.01716 -0.0023 0.2250 0.0110
-5.500 -0.5567 0.02321 0.01490 -0.0029 0.2250 0.0111
-5.250 -0.5293 0.02192 0.01364 -0.0032 0.2249 0.0112
-5.000 -0.5022 0.02099 0.01273 -0.0035 0.2249 0.0112
-4.750 -0.4751 0.02020 0.01196 -0.0037 0.2249 0.0113
-4.500 -0.4481 0.01944 0.01124 -0.0039 0.2249 0.0114
-4.250 -0.4215 0.01884 0.01065 -0.0040 0.2249 0.0114
-4.000 -0.3952 0.01827 0.01012 -0.0040 0.2249 0.0115
-3.750 -0.3696 0.01780 0.00967 -0.0039 0.2248 0.0116
-3.500 -0.3444 0.01736 0.00925 -0.0037 0.2247 0.0118
-3.250 -0.3197 0.01695 0.00886 -0.0035 0.2246 0.0120
-3.000 -0.2953 0.01663 0.00855 -0.0031 0.2247 0.0122
-2.750 -0.2709 0.01639 0.00831 -0.0028 0.2247 0.0127
-2.500 -0.2458 0.01631 0.00821 -0.0026 0.2248 0.0131
-2.250 -0.2189 0.01660 0.00841 -0.0026 0.2249 0.0134
-2.000 -0.1935 0.01644 0.00824 -0.0024 0.2245 0.0135
-1.750 -0.1682 0.01624 0.00805 -0.0021 0.2239 0.0135
-0.750 -0.0761 0.01465 0.00664 -0.0001 0.2235 0.0140
-0.500 -0.0515 0.01446 0.00646 0.0002 0.2235 0.0142
-0.250 -0.0260 0.01432 0.00633 0.0003 0.2233 0.0144
0.500 -0.0528 0.00826 0.00088 -0.0362 0.2230 0.0134
1.000 0.1061 0.01420 0.00624 0.0003 0.2220 0.0162
1.250 0.1330 0.01423 0.00628 0.0003 0.2219 0.0163
1.500 0.1589 0.01411 0.00618 0.0003 0.2217 0.0166
1.750 0.1854 0.01407 0.00615 0.0003 0.2215 0.0173
2.000 0.2124 0.01409 0.00617 0.0003 0.2211 0.0184
2.250 0.2393 0.01405 0.00615 0.0002 0.2206 0.0206
2.500 0.2662 0.01397 0.00610 0.0002 0.2199 0.0234
3.000 0.3215 0.01343 0.00571 0.0001 0.2167 0.0201
3.250 0.3485 0.01355 0.00581 0.0000 0.2138 0.0218
3.500 0.3758 0.01357 0.00585 -0.0001 0.2117 0.0206
3.750 0.4042 0.01330 0.00565 -0.0003 0.2074 0.0196
4.000 0.4307 0.01357 0.00591 -0.0004 0.2030 0.0192
4.250 0.4654 0.01243 0.00484 -0.0013 0.1692 0.0193
4.500 0.4934 0.01237 0.00457 -0.0016 0.1410 0.0202
4.750 0.5180 0.01261 0.00477 -0.0013 0.1233 0.0667
5.000 0.5422 0.01294 0.00497 -0.0010 0.0970 0.0808
5.250 0.5592 0.01147 0.00490 -0.0003 0.0807 0.6640
5.500 0.5831 0.01161 0.00520 0.0002 0.0655 0.7426
5.750 0.6090 0.01187 0.00540 0.0003 0.0543 0.7493
6.000 0.6353 0.01213 0.00560 0.0003 0.0458 0.7546
6.250 0.6608 0.01238 0.00583 0.0005 0.0376 0.7614
6.500 0.6867 0.01264 0.00607 0.0006 0.0322 0.7675
6.750 0.7126 0.01292 0.00631 0.0007 0.0266 0.7712
7.000 0.7382 0.01318 0.00656 0.0009 0.0231 0.7744
7.250 0.7634 0.01345 0.00684 0.0011 0.0199 0.7788
7.500 0.7888 0.01372 0.00713 0.0013 0.0182 0.7824
7.750 0.8140 0.01402 0.00742 0.0014 0.0166 0.7842
8.000 0.8388 0.01435 0.00775 0.0017 0.0148 0.7858
8.250 0.8639 0.01464 0.00806 0.0019 0.0142 0.7873
8.500 0.8888 0.01496 0.00840 0.0021 0.0135 0.7888
8.750 0.9132 0.01529 0.00875 0.0024 0.0126 0.7904
9.000 0.9370 0.01564 0.00912 0.0027 0.0118 0.7924
9.250 0.9602 0.01605 0.00957 0.0032 0.0110 0.7942
9.500 0.9830 0.01649 0.01005 0.0037 0.0105 0.7959
9.750 1.0064 0.01685 0.01047 0.0041 0.0103 0.7976
10.000 1.0293 0.01725 0.01092 0.0046 0.0100 0.7995
10.250 1.0518 0.01767 0.01138 0.0051 0.0097 0.8015
10.500 1.0737 0.01813 0.01188 0.0057 0.0094 0.8035
10.750 1.0954 0.01858 0.01239 0.0063 0.0090 0.8053
11.000 1.1162 0.01909 0.01294 0.0070 0.0088 0.8068
11.250 1.1365 0.01959 0.01349 0.0078 0.0085 0.8087
11.500 1.1561 0.02013 0.01408 0.0086 0.0082 0.8107
11.750 1.1735 0.02076 0.01479 0.0098 0.0079 0.8129
12.000 1.1896 0.02145 0.01555 0.0112 0.0077 0.8154
12.250 1.2007 0.02233 0.01654 0.0132 0.0074 0.8182
12.500 1.2140 0.02292 0.01720 0.0150 0.0073 0.8207
12.750 1.2300 0.02342 0.01776 0.0164 0.0072 0.8230
13.000 1.2395 0.02418 0.01860 0.0187 0.0071 0.8252
13.250 1.2529 0.02479 0.01929 0.0203 0.0070 0.8281
13.500 1.2630 0.02556 0.02016 0.0222 0.0069 0.8312
13.750 1.2722 0.02640 0.02109 0.0241 0.0068 0.8346
14.000 1.2819 0.02727 0.02205 0.0258 0.0067 0.8384
14.250 1.2895 0.02828 0.02316 0.0275 0.0065 0.8420
14.500 1.2977 0.02929 0.02426 0.0290 0.0064 0.8460
14.750 1.3031 0.03047 0.02556 0.0307 0.0063 0.8506
15.000 1.3113 0.03157 0.02675 0.0319 0.0061 0.8553
15.250 1.3147 0.03300 0.02829 0.0334 0.0061 0.8603
15.500 1.3167 0.03454 0.02996 0.0349 0.0060 0.8664
15.750 1.3213 0.03597 0.03150 0.0360 0.0059 0.8736
16.000 1.3256 0.03747 0.03312 0.0371 0.0058 0.8820
16.250 1.3231 0.03941 0.03522 0.0384 0.0058 0.8960
16.500 1.3253 0.04112 0.03716 0.0392 0.0056 0.9352
17.000 1.3273 0.04660 0.04291 0.0375 0.0056 1.0000
17.250 1.3183 0.04985 0.04628 0.0374 0.0055 1.0000
17.500 1.3055 0.05373 0.05028 0.0369 0.0054 1.0000
17.750 1.2860 0.05872 0.05543 0.0355 0.0054 1.0000
18.000 1.2473 0.06719 0.06411 0.0317 0.0055 1.0000
18.250 1.1722 0.08456 0.08180 0.0209 0.0056 1.0000
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Polar data table (+)
Polar graphs
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