GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 429 AIRFOIL (goe429-il) Reynolds number: 500,000 Max Cl/Cd: 57.23 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe429-il-500000.txt Download as CSV file: xf-goe429-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 429 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
------ -------- --------- --------- -------- -------- --------
-18.500 -1.0818 0.16148 0.15887 0.0617 1.0000 0.0152
-18.250 -1.1128 0.14894 0.14615 0.0539 1.0000 0.0151
-18.000 -1.1354 0.13907 0.13613 0.0479 1.0000 0.0151
-17.750 -1.1551 0.13029 0.12721 0.0428 1.0000 0.0150
-17.500 -1.1730 0.12216 0.11894 0.0381 1.0000 0.0151
-17.250 -1.1895 0.11452 0.11116 0.0338 1.0000 0.0151
-17.000 -1.2053 0.10721 0.10372 0.0297 1.0000 0.0151
-16.750 -1.2202 0.10024 0.09661 0.0259 1.0000 0.0152
-16.500 -1.2341 0.09360 0.08984 0.0223 1.0000 0.0152
-16.250 -1.2472 0.08729 0.08339 0.0189 1.0000 0.0153
-16.000 -1.2597 0.08123 0.07720 0.0156 1.0000 0.0154
-15.750 -1.2754 0.07535 0.07119 0.0131 1.0000 0.0155
-15.500 -1.2891 0.06979 0.06552 0.0106 1.0000 0.0156
-15.250 -1.3008 0.06460 0.06022 0.0083 1.0000 0.0158
-15.000 -1.3104 0.05969 0.05520 0.0061 1.0000 0.0159
-14.750 -1.3182 0.05508 0.05050 0.0039 1.0000 0.0161
-14.500 -1.3238 0.05082 0.04613 0.0019 1.0000 0.0163
-14.250 -1.3276 0.04690 0.04210 0.0001 1.0000 0.0165
-14.000 -1.3296 0.04331 0.03841 -0.0014 1.0000 0.0167
-13.750 -1.3298 0.04005 0.03504 -0.0028 1.0000 0.0169
-13.500 -1.3284 0.03706 0.03194 -0.0039 1.0000 0.0172
-13.250 -1.3255 0.03437 0.02911 -0.0048 1.0000 0.0175
-13.000 -1.3218 0.03206 0.02667 -0.0052 1.0000 0.0178
-12.750 -1.3170 0.03029 0.02477 -0.0043 1.0000 0.0182
-12.500 -1.3065 0.02887 0.02322 -0.0034 1.0000 0.0186
-12.250 -1.2970 0.02710 0.02135 -0.0025 1.0000 0.0190
-12.000 -1.2850 0.02546 0.01965 -0.0016 1.0000 0.0197
-11.750 -1.2678 0.02429 0.01841 -0.0011 1.0000 0.0204
-11.500 -1.2483 0.02329 0.01733 -0.0006 1.0000 0.0213
-11.250 -1.2273 0.02241 0.01635 -0.0001 1.0000 0.0223
-11.000 -1.2084 0.02117 0.01504 0.0005 1.0000 0.0235
-10.750 -1.1869 0.02023 0.01407 0.0008 1.0000 0.0249
-10.500 -1.1638 0.01945 0.01321 0.0012 1.0000 0.0266
-10.250 -1.1416 0.01847 0.01219 0.0015 1.0000 0.0288
-10.000 -1.1174 0.01776 0.01145 0.0018 1.0000 0.0318
-9.750 -1.0935 0.01695 0.01066 0.0020 1.0000 0.0365
-9.500 -1.0685 0.01629 0.01001 0.0022 1.0000 0.0428
-9.250 -1.0427 0.01576 0.00950 0.0023 1.0000 0.0495
-9.000 -1.0160 0.01539 0.00910 0.0024 1.0000 0.0550
-8.750 -0.9894 0.01497 0.00871 0.0024 1.0000 0.0604
-8.500 -0.9621 0.01466 0.00835 0.0024 1.0000 0.0646
-8.250 -0.9353 0.01424 0.00796 0.0024 1.0000 0.0697
-8.000 -0.9075 0.01401 0.00768 0.0024 1.0000 0.0736
-7.750 -0.8807 0.01351 0.00718 0.0024 1.0000 0.0781
-7.500 -0.8531 0.01318 0.00685 0.0024 1.0000 0.0826
-7.250 -0.8249 0.01297 0.00658 0.0023 1.0000 0.0862
-7.000 -0.7979 0.01242 0.00607 0.0023 1.0000 0.0920
-6.750 -0.7697 0.01214 0.00577 0.0022 1.0000 0.0976
-6.500 -0.7420 0.01171 0.00536 0.0021 1.0000 0.1043
-6.250 -0.7139 0.01133 0.00500 0.0020 1.0000 0.1109
-6.000 -0.6858 0.01091 0.00460 0.0018 1.0000 0.1187
-5.750 -0.6575 0.01051 0.00424 0.0017 1.0000 0.1290
-5.500 -0.6294 0.00999 0.00390 0.0014 1.0000 0.1535
-5.250 -0.6011 0.00953 0.00364 0.0011 1.0000 0.1947
-5.000 -0.5720 0.00922 0.00343 0.0008 1.0000 0.2199
-4.750 -0.5428 0.00894 0.00323 0.0004 1.0000 0.2406
-4.500 -0.5131 0.00868 0.00305 0.0000 1.0000 0.2593
-4.250 -0.4793 0.00849 0.00292 -0.0013 0.9643 0.2785
-4.000 -0.4538 0.00840 0.00285 -0.0005 0.9199 0.2991
-3.750 -0.4301 0.00831 0.00275 0.0008 0.8890 0.3222
-3.500 -0.4042 0.00819 0.00264 0.0014 0.8650 0.3458
-3.250 -0.3774 0.00809 0.00254 0.0019 0.8450 0.3710
-3.000 -0.3497 0.00796 0.00244 0.0021 0.8264 0.3962
-2.750 -0.3217 0.00788 0.00235 0.0023 0.8092 0.4196
-2.500 -0.2936 0.00779 0.00226 0.0025 0.7912 0.4400
-2.250 -0.2653 0.00772 0.00219 0.0026 0.7745 0.4613
-2.000 -0.2368 0.00766 0.00212 0.0027 0.7609 0.4813
-1.750 -0.2080 0.00760 0.00207 0.0027 0.7482 0.5004
-1.500 -0.1791 0.00752 0.00202 0.0027 0.7360 0.5197
-1.250 -0.1503 0.00746 0.00199 0.0027 0.7241 0.5392
-1.000 -0.1216 0.00741 0.00198 0.0028 0.7116 0.5613
-0.750 -0.0929 0.00738 0.00197 0.0029 0.6968 0.5842
-0.500 -0.0640 0.00736 0.00197 0.0029 0.6817 0.6039
-0.250 -0.0349 0.00735 0.00199 0.0029 0.6673 0.6219
0.000 -0.0057 0.00735 0.00200 0.0029 0.6524 0.6380
0.250 0.0234 0.00737 0.00200 0.0029 0.6357 0.6521
0.500 0.0526 0.00740 0.00201 0.0029 0.6175 0.6652
0.750 0.0817 0.00743 0.00202 0.0029 0.5965 0.6772
1.000 0.1107 0.00747 0.00202 0.0029 0.5696 0.6880
1.250 0.1397 0.00757 0.00203 0.0029 0.5350 0.6986
1.500 0.1686 0.00772 0.00206 0.0029 0.4899 0.7099
1.750 0.1971 0.00793 0.00212 0.0028 0.4401 0.7221
2.000 0.2256 0.00820 0.00222 0.0027 0.3892 0.7340
2.250 0.2543 0.00846 0.00232 0.0026 0.3437 0.7454
2.500 0.2828 0.00868 0.00243 0.0025 0.3066 0.7569
2.750 0.3112 0.00888 0.00255 0.0024 0.2749 0.7680
3.000 0.3397 0.00906 0.00267 0.0024 0.2501 0.7790
3.500 0.3964 0.00939 0.00294 0.0023 0.2132 0.8012
3.750 0.4246 0.00951 0.00307 0.0023 0.2001 0.8144
4.000 0.4524 0.00960 0.00322 0.0025 0.1886 0.8307
4.250 0.4793 0.00968 0.00337 0.0029 0.1778 0.8538
4.500 0.5035 0.00971 0.00351 0.0039 0.1666 0.8965
4.750 0.5356 0.00977 0.00362 0.0033 0.1526 1.0000
5.000 0.5648 0.01001 0.00378 0.0030 0.1371 1.0000
5.250 0.5935 0.01037 0.00399 0.0027 0.1083 1.0000
5.500 0.6206 0.01124 0.00451 0.0024 0.0568 1.0000
5.750 0.6490 0.01163 0.00491 0.0022 0.0526 1.0000
6.000 0.6771 0.01208 0.00537 0.0021 0.0496 1.0000
6.250 0.7047 0.01265 0.00595 0.0021 0.0471 1.0000
6.500 0.7322 0.01317 0.00651 0.0020 0.0457 1.0000
6.750 0.7598 0.01361 0.00699 0.0020 0.0447 1.0000
7.000 0.7870 0.01411 0.00754 0.0020 0.0437 1.0000
7.250 0.8138 0.01466 0.00811 0.0020 0.0424 1.0000
7.500 0.8402 0.01526 0.00873 0.0021 0.0412 1.0000
7.750 0.8660 0.01597 0.00947 0.0022 0.0402 1.0000
8.000 0.8902 0.01697 0.01049 0.0024 0.0392 1.0000
8.250 0.9134 0.01819 0.01175 0.0027 0.0383 1.0000
8.500 0.9395 0.01869 0.01232 0.0029 0.0377 1.0000
8.750 0.9649 0.01932 0.01301 0.0031 0.0370 1.0000
9.000 0.9894 0.02008 0.01383 0.0034 0.0362 1.0000
9.250 1.0136 0.02089 0.01469 0.0037 0.0354 1.0000
9.500 1.0374 0.02169 0.01554 0.0040 0.0346 1.0000
9.750 1.0607 0.02254 0.01642 0.0043 0.0337 1.0000
10.000 1.0825 0.02370 0.01757 0.0047 0.0329 1.0000
10.250 1.1005 0.02626 0.02017 0.0053 0.0319 1.0000
10.500 1.1233 0.02680 0.02084 0.0057 0.0314 1.0000
10.750 1.1450 0.02756 0.02174 0.0061 0.0308 1.0000
11.000 1.1656 0.02851 0.02281 0.0066 0.0300 1.0000
11.250 1.1851 0.02959 0.02399 0.0071 0.0292 1.0000
11.500 1.2038 0.03071 0.02518 0.0077 0.0286 1.0000
11.750 1.2210 0.03185 0.02641 0.0083 0.0279 1.0000
12.000 1.2375 0.03309 0.02769 0.0088 0.0274 1.0000
12.250 1.2499 0.03561 0.03024 0.0095 0.0266 1.0000
12.500 1.2573 0.03753 0.03238 0.0105 0.0261 1.0000
12.750 1.2627 0.03891 0.03396 0.0117 0.0257 1.0000
13.000 1.2625 0.04080 0.03602 0.0128 0.0252 1.0000
13.250 1.2611 0.04319 0.03859 0.0129 0.0248 1.0000
13.500 1.2588 0.04599 0.04155 0.0124 0.0245 1.0000
13.750 1.2558 0.04912 0.04483 0.0113 0.0241 1.0000
14.000 1.2522 0.05252 0.04836 0.0098 0.0238 1.0000
14.250 1.2480 0.05619 0.05215 0.0080 0.0235 1.0000
14.500 1.2433 0.06008 0.05616 0.0058 0.0233 1.0000
14.750 1.2354 0.06464 0.06084 0.0031 0.0231 1.0000
15.000 1.2256 0.06971 0.06604 -0.0001 0.0229 1.0000
15.250 1.2138 0.07533 0.07178 -0.0037 0.0227 1.0000
15.500 1.1986 0.08172 0.07831 -0.0079 0.0226 1.0000
15.750 1.1796 0.08907 0.08580 -0.0126 0.0225 1.0000
16.000 1.1524 0.09848 0.09540 -0.0188 0.0225 1.0000
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Polar data table (+)
Polar graphs
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