GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 200,000 Max Cl/Cd: 73.59 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe176-il-200000-n5.txt Download as CSV file: xf-goe176-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 176 (ALBATROS 7020) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2867 0.10773 0.10433 -0.0346 1.0000 0.0238
-9.000 -0.2846 0.10463 0.10128 -0.0351 1.0000 0.0238
-8.750 -0.2834 0.10156 0.09826 -0.0353 1.0000 0.0238
-8.250 -0.1770 0.07409 0.07107 -0.0468 0.9781 0.0161
-7.750 -0.2742 0.08540 0.08226 -0.0378 0.9936 0.0158
-7.500 -0.2601 0.08102 0.07791 -0.0424 0.9821 0.0155
-7.250 -0.2473 0.07644 0.07334 -0.0471 0.9627 0.0152
-7.000 -0.2300 0.07108 0.06799 -0.0539 0.9430 0.0150
-6.750 -0.2030 0.06404 0.06091 -0.0646 0.9279 0.0147
-6.500 -0.1677 0.05450 0.05127 -0.0800 0.9142 0.0145
-6.250 -0.1063 0.02920 0.02480 -0.1165 0.9011 0.0140
-6.000 -0.0634 0.02481 0.01964 -0.1230 0.8891 0.0154
-5.750 -0.0240 0.02194 0.01609 -0.1268 0.8751 0.0161
-5.500 0.0116 0.01970 0.01334 -0.1291 0.8600 0.0167
-5.250 0.0435 0.01796 0.01131 -0.1305 0.8453 0.0176
-5.000 0.0739 0.01701 0.01017 -0.1311 0.8312 0.0188
-4.750 0.1034 0.01636 0.00932 -0.1315 0.8166 0.0211
-4.500 0.1323 0.01563 0.00837 -0.1315 0.8017 0.0229
-4.250 0.1607 0.01483 0.00737 -0.1315 0.7862 0.0245
-4.000 0.1886 0.01420 0.00663 -0.1316 0.7698 0.0277
-3.750 0.2167 0.01381 0.00607 -0.1315 0.7540 0.0318
-3.500 0.2451 0.01331 0.00538 -0.1315 0.7395 0.0363
-3.250 0.2732 0.01296 0.00484 -0.1314 0.7254 0.0440
-3.000 0.3014 0.01254 0.00432 -0.1313 0.7115 0.0575
-2.750 0.3290 0.01196 0.00404 -0.1314 0.6965 0.1453
-2.500 0.3564 0.01201 0.00403 -0.1311 0.6804 0.1888
-2.250 0.3837 0.01207 0.00395 -0.1308 0.6654 0.2047
-2.000 0.4111 0.01214 0.00388 -0.1305 0.6516 0.2183
-1.750 0.4384 0.01224 0.00383 -0.1301 0.6372 0.2320
-1.250 0.4924 0.01234 0.00373 -0.1295 0.6075 0.2508
-1.000 0.5194 0.01237 0.00365 -0.1291 0.5924 0.2567
-0.750 0.5463 0.01243 0.00358 -0.1288 0.5779 0.2631
-0.500 0.5733 0.01245 0.00356 -0.1285 0.5648 0.2696
-0.250 0.6004 0.01252 0.00353 -0.1282 0.5524 0.2778
0.000 0.6273 0.01256 0.00354 -0.1279 0.5399 0.2849
0.250 0.6541 0.01263 0.00354 -0.1276 0.5268 0.2923
0.500 0.6807 0.01269 0.00357 -0.1273 0.5123 0.2988
0.750 0.7072 0.01278 0.00360 -0.1269 0.4948 0.3063
1.000 0.7334 0.01287 0.00365 -0.1265 0.4734 0.3146
1.250 0.7591 0.01300 0.00371 -0.1261 0.4459 0.3253
1.500 0.7837 0.01322 0.00378 -0.1255 0.4085 0.3380
2.000 0.8320 0.01377 0.00411 -0.1242 0.3608 0.3766
2.250 0.8568 0.01398 0.00434 -0.1237 0.3490 0.4165
2.500 0.8819 0.01408 0.00456 -0.1233 0.3397 0.4893
3.000 0.9258 0.01368 0.00492 -0.1206 0.3255 1.0000
3.250 0.9509 0.01403 0.00515 -0.1201 0.3193 1.0000
3.500 0.9771 0.01425 0.00536 -0.1198 0.3146 1.0000
3.750 1.0028 0.01452 0.00561 -0.1194 0.3094 1.0000
4.000 1.0275 0.01486 0.00588 -0.1189 0.3038 1.0000
4.250 1.0537 0.01507 0.00611 -0.1186 0.2978 1.0000
4.500 1.0789 0.01535 0.00639 -0.1182 0.2921 1.0000
4.750 1.1039 0.01565 0.00667 -0.1177 0.2877 1.0000
5.000 1.1298 0.01585 0.00694 -0.1173 0.2832 1.0000
5.250 1.1551 0.01611 0.00722 -0.1169 0.2778 1.0000
5.500 1.1796 0.01641 0.00754 -0.1164 0.2727 1.0000
5.750 1.2052 0.01662 0.00784 -0.1160 0.2675 1.0000
6.000 1.2300 0.01689 0.00815 -0.1155 0.2622 1.0000
6.250 1.2545 0.01717 0.00850 -0.1150 0.2572 1.0000
6.500 1.2794 0.01742 0.00884 -0.1145 0.2505 1.0000
6.750 1.3033 0.01772 0.00919 -0.1139 0.2427 1.0000
7.000 1.3269 0.01803 0.00953 -0.1133 0.2267 1.0000
7.250 1.3393 0.01924 0.01022 -0.1112 0.1552 1.0000
7.500 1.3548 0.02030 0.01115 -0.1095 0.1299 1.0000
7.750 1.3714 0.02120 0.01197 -0.1080 0.1107 1.0000
8.000 1.3842 0.02236 0.01294 -0.1060 0.0688 1.0000
8.250 1.3963 0.02349 0.01399 -0.1038 0.0592 1.0000
8.500 1.4094 0.02445 0.01501 -0.1018 0.0545 1.0000
8.750 1.4236 0.02518 0.01585 -0.0998 0.0502 1.0000
9.000 1.4356 0.02601 0.01678 -0.0976 0.0458 1.0000
9.250 1.4486 0.02681 0.01770 -0.0955 0.0404 1.0000
9.500 1.4566 0.02795 0.01877 -0.0930 0.0191 1.0000
9.750 1.4606 0.02944 0.02029 -0.0901 0.0161 1.0000
10.000 1.4667 0.03085 0.02182 -0.0877 0.0144 1.0000
10.250 1.4727 0.03233 0.02345 -0.0855 0.0134 1.0000
10.500 1.4780 0.03395 0.02524 -0.0836 0.0127 1.0000
10.750 1.4811 0.03585 0.02732 -0.0817 0.0119 1.0000
11.000 1.4823 0.03806 0.02969 -0.0801 0.0112 1.0000
11.250 1.4812 0.04062 0.03243 -0.0787 0.0107 1.0000
11.500 1.4784 0.04352 0.03551 -0.0776 0.0104 1.0000
11.750 1.4731 0.04685 0.03901 -0.0768 0.0101 1.0000
12.000 1.4650 0.05070 0.04304 -0.0764 0.0098 1.0000
12.250 1.4547 0.05503 0.04760 -0.0764 0.0096 1.0000
12.500 1.4431 0.05971 0.05244 -0.0766 0.0095 1.0000
12.750 1.4335 0.06428 0.05717 -0.0771 0.0094 1.0000
13.000 1.4252 0.06879 0.06183 -0.0777 0.0093 1.0000
13.250 1.4159 0.07353 0.06672 -0.0785 0.0092 1.0000
13.500 1.4066 0.07842 0.07176 -0.0794 0.0091 1.0000
13.750 1.3974 0.08338 0.07686 -0.0805 0.0089 1.0000
14.000 1.3884 0.08840 0.08200 -0.0816 0.0088 1.0000
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Polar data table (+)
Polar graphs
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