GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 500,000 Max Cl/Cd: 95.53 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe346-il-500000.txt Download as CSV file: xf-goe346-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3326 0.09111 0.08893 -0.0226 1.0000 0.0185
-8.500 -0.3334 0.08768 0.08551 -0.0246 1.0000 0.0185
-8.000 -0.4139 0.09395 0.09169 -0.0200 1.0000 0.0185
-7.750 -0.4035 0.08997 0.08772 -0.0256 1.0000 0.0185
-7.500 -0.3978 0.08548 0.08325 -0.0250 1.0000 0.0187
-7.250 -0.3908 0.08221 0.08000 -0.0239 1.0000 0.0189
-7.000 -0.3828 0.07928 0.07708 -0.0247 1.0000 0.0192
-6.750 -0.3758 0.07654 0.07436 -0.0258 1.0000 0.0195
-6.500 -0.3717 0.07414 0.07198 -0.0261 1.0000 0.0199
-6.250 -0.3728 0.07212 0.06998 -0.0251 1.0000 0.0204
-6.000 -0.3522 0.06842 0.06625 -0.0296 0.9983 0.0214
-5.750 -0.2944 0.06278 0.06039 -0.0444 0.9951 0.0229
-5.500 -0.2557 0.05800 0.05545 -0.0513 0.9922 0.0230
-5.250 -0.2323 0.05210 0.04950 -0.0554 0.9890 0.0235
-5.000 -0.2059 0.04894 0.04633 -0.0583 0.9865 0.0239
-4.750 -0.1715 0.04568 0.04300 -0.0627 0.9844 0.0247
-4.500 -0.1353 0.04239 0.03958 -0.0670 0.9810 0.0260
-4.250 -0.0860 0.03975 0.03663 -0.0716 0.9771 0.0286
-4.000 -0.0468 0.03706 0.03368 -0.0746 0.9737 0.0289
-3.750 -0.0169 0.03154 0.02801 -0.0781 0.9706 0.0296
-3.500 0.0090 0.02941 0.02583 -0.0793 0.9639 0.0302
-3.250 0.0384 0.02752 0.02385 -0.0806 0.9586 0.0310
-3.000 0.0669 0.02578 0.02199 -0.0814 0.9519 0.0321
-2.750 0.0957 0.02418 0.02022 -0.0816 0.9447 0.0340
-2.500 0.1287 0.02425 0.01996 -0.0807 0.9374 0.0365
-2.250 0.1553 0.02111 0.01649 -0.0808 0.9297 0.0372
-2.000 0.1797 0.01906 0.01440 -0.0810 0.9215 0.0383
-1.750 0.2050 0.01797 0.01323 -0.0807 0.9133 0.0394
-1.500 0.2309 0.01703 0.01218 -0.0803 0.9030 0.0410
-1.250 0.2574 0.01624 0.01123 -0.0796 0.8923 0.0436
-1.000 0.2852 0.01708 0.01181 -0.0783 0.8802 0.0465
-0.750 0.3106 0.01433 0.00889 -0.0782 0.8675 0.0489
-0.500 0.3366 0.01357 0.00806 -0.0778 0.8526 0.0507
-0.250 0.3634 0.01302 0.00739 -0.0773 0.8378 0.0540
0.000 0.3915 0.01386 0.00806 -0.0766 0.8243 0.0582
1.250 0.5289 0.00967 0.00339 -0.0748 0.7546 0.0477
1.500 0.5561 0.00940 0.00310 -0.0745 0.7386 0.0458
1.750 0.5831 0.00906 0.00272 -0.0742 0.7220 0.0453
2.000 0.6101 0.00889 0.00250 -0.0739 0.7025 0.0457
2.250 0.6367 0.00885 0.00237 -0.0735 0.6745 0.0465
2.500 0.6632 0.00872 0.00215 -0.0731 0.6395 0.0479
2.750 0.6890 0.00880 0.00206 -0.0727 0.5913 0.0513
3.000 0.7143 0.00905 0.00207 -0.0722 0.5378 0.0543
3.250 0.7399 0.00931 0.00213 -0.0718 0.4921 0.0578
3.500 0.7656 0.00905 0.00234 -0.0718 0.4419 0.4310
3.750 0.7862 0.00823 0.00250 -0.0704 0.3859 1.0000
4.000 0.8108 0.00876 0.00272 -0.0700 0.3299 1.0000
4.250 0.8358 0.00925 0.00297 -0.0696 0.2847 1.0000
4.500 0.8612 0.00966 0.00322 -0.0693 0.2506 1.0000
4.750 0.8868 0.01004 0.00347 -0.0691 0.2223 1.0000
5.000 0.9123 0.01041 0.00372 -0.0688 0.1980 1.0000
5.250 0.9376 0.01082 0.00400 -0.0684 0.1723 1.0000
5.500 0.9621 0.01134 0.00434 -0.0680 0.1326 1.0000
5.750 0.9828 0.01247 0.00499 -0.0672 0.0544 1.0000
6.000 1.0071 0.01304 0.00549 -0.0666 0.0430 1.0000
6.250 1.0315 0.01357 0.00604 -0.0661 0.0390 1.0000
6.500 1.0550 0.01425 0.00679 -0.0654 0.0355 1.0000
6.750 1.0789 0.01482 0.00743 -0.0647 0.0337 1.0000
7.000 1.1025 0.01540 0.00807 -0.0641 0.0316 1.0000
7.250 1.1249 0.01613 0.00886 -0.0633 0.0297 1.0000
7.500 1.1451 0.01718 0.00997 -0.0622 0.0277 1.0000
7.750 1.1630 0.01855 0.01144 -0.0607 0.0259 1.0000
8.000 1.1862 0.01906 0.01203 -0.0601 0.0246 1.0000
8.250 1.2076 0.01987 0.01290 -0.0591 0.0232 1.0000
8.500 1.2282 0.02073 0.01382 -0.0581 0.0220 1.0000
8.750 1.2474 0.02178 0.01491 -0.0570 0.0209 1.0000
9.000 1.2604 0.02439 0.01759 -0.0551 0.0195 1.0000
9.250 1.2826 0.02470 0.01802 -0.0543 0.0188 1.0000
9.500 1.3025 0.02559 0.01902 -0.0532 0.0179 1.0000
9.750 1.3211 0.02670 0.02024 -0.0520 0.0171 1.0000
10.000 1.3389 0.02779 0.02145 -0.0508 0.0164 1.0000
10.250 1.3557 0.02890 0.02264 -0.0495 0.0158 1.0000
10.500 1.3706 0.03044 0.02424 -0.0481 0.0153 1.0000
10.750 1.3792 0.03427 0.02829 -0.0461 0.0146 1.0000
11.000 1.3914 0.03523 0.02947 -0.0441 0.0143 1.0000
11.250 1.4010 0.03669 0.03115 -0.0419 0.0138 1.0000
11.500 1.4068 0.03851 0.03321 -0.0394 0.0133 1.0000
11.750 1.4065 0.04059 0.03550 -0.0362 0.0130 1.0000
12.000 1.4036 0.04285 0.03796 -0.0330 0.0127 1.0000
12.250 1.3986 0.04533 0.04064 -0.0302 0.0125 1.0000
12.500 1.3926 0.04796 0.04346 -0.0280 0.0123 1.0000
12.750 1.3846 0.05095 0.04664 -0.0262 0.0122 1.0000
13.000 1.3749 0.05434 0.05022 -0.0251 0.0121 1.0000
13.250 1.3646 0.05800 0.05405 -0.0246 0.0120 1.0000
13.500 1.3502 0.06258 0.05882 -0.0249 0.0119 1.0000
13.750 1.3334 0.06787 0.06431 -0.0262 0.0119 1.0000
14.000 1.3100 0.07478 0.07146 -0.0288 0.0119 1.0000
14.250 1.2712 0.08544 0.08244 -0.0344 0.0121 1.0000
14.500 1.2329 0.09743 0.09471 -0.0420 0.0124 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)