GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.2 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe376-il-1000000-n5.txt Download as CSV file: xf-goe376-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3375 0.10006 0.09847 -0.0193 1.0000 0.0048
-8.750 -0.3378 0.09650 0.09493 -0.0198 1.0000 0.0049
-8.500 -0.3396 0.09302 0.09147 -0.0202 1.0000 0.0052
-8.250 -0.3246 0.08886 0.08732 -0.0249 0.9983 0.0052
-8.000 -0.3074 0.08620 0.08466 -0.0284 0.9946 0.0054
-7.750 -0.2930 0.08363 0.08210 -0.0313 0.9892 0.0057
-7.250 -0.2648 0.07592 0.07439 -0.0400 0.9591 0.0061
-7.000 -0.2248 0.06661 0.06499 -0.0562 0.9425 0.0071
-6.750 -0.1597 0.06112 0.05938 -0.0723 0.9253 0.0074
-6.500 -0.1161 0.05802 0.05611 -0.0810 0.8959 0.0082
-6.250 -0.0985 0.05366 0.05159 -0.0853 0.8683 0.0090
-6.000 -0.0832 0.04857 0.04634 -0.0891 0.8462 0.0096
-5.750 -0.0640 0.04703 0.04469 -0.0900 0.8243 0.0099
-5.500 -0.0450 0.04497 0.04249 -0.0910 0.8008 0.0101
-5.250 -0.0252 0.04295 0.04032 -0.0918 0.7769 0.0107
-5.000 -0.0033 0.03646 0.03354 -0.0949 0.7592 0.0124
-4.750 0.0185 0.03510 0.03206 -0.0952 0.7429 0.0126
-4.250 0.0643 0.03199 0.02872 -0.0957 0.7174 0.0132
-4.000 0.0881 0.03014 0.02673 -0.0959 0.7062 0.0141
-3.750 0.1132 0.02465 0.02082 -0.0957 0.6969 0.0158
-3.500 0.1365 0.02372 0.01978 -0.0955 0.6851 0.0160
-3.250 0.1604 0.02313 0.01911 -0.0952 0.6738 0.0164
-3.000 0.1846 0.02208 0.01794 -0.0949 0.6636 0.0169
-2.750 0.2089 0.02053 0.01620 -0.0943 0.6526 0.0174
-2.500 0.2333 0.01893 0.01438 -0.0935 0.6399 0.0179
-2.250 0.2574 0.01713 0.01231 -0.0924 0.6244 0.0184
-2.000 0.2812 0.01466 0.00937 -0.0908 0.6078 0.0199
-1.750 0.3051 0.01404 0.00858 -0.0901 0.5835 0.0201
-1.500 0.3289 0.01361 0.00797 -0.0894 0.5541 0.0204
-1.250 0.3528 0.01321 0.00737 -0.0886 0.5233 0.0207
-1.000 0.3770 0.01276 0.00670 -0.0878 0.4940 0.0209
-0.750 0.4017 0.01225 0.00600 -0.0871 0.4743 0.0211
-0.250 0.4526 0.01143 0.00491 -0.0859 0.4470 0.0216
0.000 0.4783 0.01097 0.00432 -0.0853 0.4369 0.0215
0.250 0.5039 0.01056 0.00378 -0.0847 0.4266 0.0214
0.500 0.5296 0.01022 0.00336 -0.0841 0.4172 0.0214
0.750 0.5554 0.00996 0.00304 -0.0836 0.4099 0.0217
1.000 0.5813 0.00976 0.00279 -0.0831 0.4027 0.0223
1.250 0.6071 0.00961 0.00260 -0.0826 0.3963 0.0228
1.500 0.6330 0.00950 0.00246 -0.0821 0.3884 0.0233
1.750 0.6585 0.00946 0.00237 -0.0816 0.3771 0.0237
2.000 0.6839 0.00941 0.00228 -0.0811 0.3666 0.0239
2.250 0.7095 0.00940 0.00224 -0.0806 0.3554 0.0241
2.750 0.7597 0.00935 0.00211 -0.0794 0.3291 0.0249
3.000 0.7846 0.00934 0.00206 -0.0788 0.3157 0.0251
3.250 0.8095 0.00940 0.00206 -0.0782 0.3010 0.0252
3.500 0.8344 0.00947 0.00209 -0.0777 0.2867 0.0253
3.750 0.8591 0.00956 0.00213 -0.0770 0.2722 0.0256
4.000 0.8838 0.00968 0.00220 -0.0764 0.2594 0.0262
4.250 0.9086 0.00981 0.00229 -0.0759 0.2478 0.0270
4.500 0.9331 0.00998 0.00242 -0.0752 0.2344 0.0281
4.750 0.9569 0.01022 0.00258 -0.0745 0.2156 0.0293
5.000 0.9813 0.01043 0.00273 -0.0739 0.2034 0.0300
5.250 1.0059 0.01060 0.00289 -0.0733 0.1936 0.0309
5.500 1.0303 0.01080 0.00306 -0.0727 0.1821 0.0328
5.750 1.0538 0.01106 0.00326 -0.0720 0.1662 0.0342
6.000 1.0756 0.01149 0.00354 -0.0710 0.1390 0.0372
6.500 1.1547 0.01188 0.00505 -0.0784 0.0493 1.0000
6.750 1.1720 0.01270 0.00569 -0.0766 0.0161 1.0000
7.000 1.1946 0.01301 0.00603 -0.0757 0.0131 1.0000
7.250 1.2165 0.01338 0.00642 -0.0747 0.0110 1.0000
7.500 1.2386 0.01372 0.00680 -0.0737 0.0097 1.0000
7.750 1.2607 0.01405 0.00716 -0.0728 0.0088 1.0000
8.000 1.2821 0.01443 0.00757 -0.0717 0.0079 1.0000
8.250 1.3027 0.01486 0.00803 -0.0705 0.0072 1.0000
8.500 1.3226 0.01535 0.00856 -0.0692 0.0066 1.0000
8.750 1.3432 0.01575 0.00901 -0.0681 0.0062 1.0000
9.000 1.3633 0.01618 0.00948 -0.0669 0.0058 1.0000
9.250 1.3827 0.01664 0.00999 -0.0656 0.0054 1.0000
9.500 1.4016 0.01713 0.01050 -0.0642 0.0050 1.0000
9.750 1.4184 0.01776 0.01118 -0.0625 0.0046 1.0000
10.000 1.4345 0.01841 0.01189 -0.0607 0.0044 1.0000
10.250 1.4512 0.01896 0.01251 -0.0591 0.0043 1.0000
10.500 1.4666 0.01958 0.01321 -0.0572 0.0041 1.0000
10.750 1.4792 0.02025 0.01394 -0.0549 0.0039 1.0000
11.000 1.4888 0.02098 0.01475 -0.0520 0.0038 1.0000
11.250 1.5010 0.02158 0.01540 -0.0497 0.0036 1.0000
11.500 1.5088 0.02247 0.01638 -0.0469 0.0035 1.0000
11.750 1.5190 0.02325 0.01723 -0.0447 0.0034 1.0000
12.000 1.5273 0.02419 0.01825 -0.0423 0.0033 1.0000
12.250 1.5331 0.02533 0.01949 -0.0399 0.0032 1.0000
12.500 1.5398 0.02650 0.02072 -0.0378 0.0031 1.0000
12.750 1.5440 0.02791 0.02222 -0.0357 0.0030 1.0000
13.000 1.5440 0.02978 0.02420 -0.0337 0.0029 1.0000
13.250 1.5410 0.03207 0.02661 -0.0319 0.0028 1.0000
13.500 1.5425 0.03414 0.02878 -0.0308 0.0027 1.0000
13.750 1.5473 0.03601 0.03075 -0.0300 0.0027 1.0000
14.000 1.5406 0.03925 0.03413 -0.0294 0.0027 1.0000
14.250 1.5375 0.04232 0.03731 -0.0292 0.0026 1.0000
14.500 1.5336 0.04561 0.04072 -0.0293 0.0026 1.0000
14.750 1.5257 0.04959 0.04483 -0.0298 0.0026 1.0000
15.000 1.5214 0.05324 0.04860 -0.0304 0.0025 1.0000
15.250 1.5113 0.05785 0.05333 -0.0315 0.0025 1.0000
15.500 1.4973 0.06322 0.05885 -0.0330 0.0025 1.0000
15.750 1.4863 0.06832 0.06407 -0.0345 0.0024 1.0000
16.000 1.4765 0.07336 0.06922 -0.0362 0.0024 1.0000
16.250 1.4618 0.07928 0.07526 -0.0382 0.0024 1.0000
16.500 1.4428 0.08591 0.08202 -0.0405 0.0024 1.0000
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Polar data table (+)
Polar graphs
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