GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il) Reynolds number: 200,000 Max Cl/Cd: 66.85 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe677-il-200000.txt Download as CSV file: xf-goe677-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 677 (= M 6) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4100 0.09618 0.09279 -0.0205 1.0000 0.0734
-9.750 -0.4031 0.09324 0.08986 -0.0203 1.0000 0.0754
-9.500 -0.5639 0.08814 0.08467 -0.0272 1.0000 0.0718
-9.250 -0.5442 0.08739 0.08393 -0.0223 1.0000 0.0730
-9.000 -0.5373 0.08465 0.08120 -0.0223 1.0000 0.0745
-8.750 -0.5415 0.08027 0.07683 -0.0253 1.0000 0.0761
-8.500 -0.5524 0.07584 0.07239 -0.0273 1.0000 0.0777
-8.250 -0.5653 0.07097 0.06745 -0.0292 1.0000 0.0803
-8.000 -0.6065 0.06699 0.06275 -0.0293 1.0000 0.0838
-7.750 -0.5957 0.05974 0.05574 -0.0298 1.0000 0.0855
-7.500 -0.5813 0.05733 0.05340 -0.0289 1.0000 0.0868
-7.250 -0.5707 0.05501 0.05105 -0.0278 1.0000 0.0887
-7.000 -0.5641 0.05248 0.04845 -0.0262 1.0000 0.0916
-6.750 -0.5867 0.04973 0.04512 -0.0206 1.0000 0.0987
-6.500 -0.5614 0.04654 0.04213 -0.0222 0.9953 0.1008
-6.250 -0.5416 0.03389 0.02794 -0.0223 0.9830 0.0693
-6.000 -0.5084 0.03029 0.02393 -0.0244 0.9712 0.0689
-5.750 -0.4742 0.02757 0.02078 -0.0261 0.9575 0.0692
-5.500 -0.4405 0.02524 0.01808 -0.0274 0.9426 0.0694
-5.250 -0.4091 0.02365 0.01615 -0.0279 0.9262 0.0700
-5.000 -0.3821 0.02194 0.01413 -0.0275 0.9093 0.0715
-4.750 -0.3569 0.02050 0.01257 -0.0269 0.8927 0.0736
-4.500 -0.3321 0.01962 0.01156 -0.0261 0.8768 0.0753
-4.250 -0.3068 0.01883 0.01064 -0.0253 0.8621 0.0772
-4.000 -0.2809 0.01811 0.00980 -0.0246 0.8489 0.0795
-3.750 -0.2548 0.01758 0.00911 -0.0239 0.8373 0.0825
-3.500 -0.2293 0.01668 0.00813 -0.0233 0.8269 0.0861
-3.250 -0.2037 0.01608 0.00755 -0.0227 0.8163 0.0902
-3.000 -0.1777 0.01562 0.00703 -0.0222 0.8077 0.0949
-2.750 -0.1525 0.01505 0.00645 -0.0216 0.7996 0.1007
-2.500 -0.1268 0.01472 0.00613 -0.0211 0.7918 0.1090
-2.250 -0.1019 0.01430 0.00573 -0.0204 0.7841 0.1183
-2.000 -0.0766 0.01396 0.00542 -0.0198 0.7773 0.1316
-1.750 -0.0518 0.01356 0.00510 -0.0192 0.7699 0.1540
-1.500 -0.0319 0.01263 0.00472 -0.0179 0.7638 0.2631
-1.250 -0.0100 0.01086 0.00538 -0.0150 0.7568 0.8826
-1.000 0.0335 0.01161 0.00599 -0.0164 0.7502 0.9335
-0.750 0.1051 0.01230 0.00652 -0.0243 0.7430 0.9608
-0.500 0.1763 0.01266 0.00670 -0.0326 0.7353 0.9839
-0.250 0.2522 0.01255 0.00645 -0.0426 0.7268 1.0000
0.000 0.2773 0.01251 0.00631 -0.0422 0.7189 1.0000
0.250 0.3027 0.01249 0.00623 -0.0420 0.7112 1.0000
0.500 0.3279 0.01248 0.00613 -0.0416 0.7029 1.0000
0.750 0.3533 0.01248 0.00607 -0.0413 0.6944 1.0000
1.000 0.3784 0.01248 0.00599 -0.0408 0.6857 1.0000
1.250 0.4039 0.01249 0.00597 -0.0405 0.6765 1.0000
1.500 0.4290 0.01251 0.00591 -0.0400 0.6680 1.0000
1.750 0.4544 0.01251 0.00591 -0.0397 0.6574 1.0000
2.000 0.4797 0.01255 0.00588 -0.0392 0.6480 1.0000
2.250 0.5049 0.01256 0.00585 -0.0388 0.6373 1.0000
2.500 0.5299 0.01256 0.00585 -0.0383 0.6253 1.0000
2.750 0.5549 0.01256 0.00580 -0.0377 0.6133 1.0000
3.000 0.5797 0.01255 0.00573 -0.0371 0.6014 1.0000
3.250 0.6045 0.01253 0.00568 -0.0365 0.5881 1.0000
3.500 0.6291 0.01250 0.00566 -0.0359 0.5743 1.0000
3.750 0.6538 0.01249 0.00564 -0.0353 0.5606 1.0000
4.000 0.6785 0.01250 0.00565 -0.0347 0.5480 1.0000
4.250 0.7033 0.01254 0.00567 -0.0342 0.5365 1.0000
4.500 0.7278 0.01258 0.00569 -0.0335 0.5245 1.0000
4.750 0.7520 0.01264 0.00576 -0.0329 0.5107 1.0000
5.000 0.7758 0.01271 0.00582 -0.0321 0.4964 1.0000
5.250 0.7995 0.01283 0.00593 -0.0314 0.4830 1.0000
5.500 0.8231 0.01299 0.00609 -0.0307 0.4706 1.0000
5.750 0.8462 0.01318 0.00625 -0.0298 0.4569 1.0000
6.000 0.8690 0.01340 0.00645 -0.0290 0.4437 1.0000
6.250 0.8915 0.01366 0.00669 -0.0281 0.4310 1.0000
6.500 0.9137 0.01391 0.00695 -0.0271 0.4175 1.0000
6.750 0.9353 0.01415 0.00723 -0.0260 0.4026 1.0000
7.000 0.9563 0.01441 0.00751 -0.0249 0.3861 1.0000
7.250 0.9768 0.01465 0.00781 -0.0236 0.3667 1.0000
7.500 0.9961 0.01490 0.00809 -0.0221 0.3411 1.0000
7.750 1.0132 0.01528 0.00840 -0.0204 0.3008 1.0000
8.000 1.0243 0.01612 0.00891 -0.0178 0.2409 1.0000
8.250 1.0319 0.01726 0.00973 -0.0148 0.1927 1.0000
8.500 1.0416 0.01823 0.01052 -0.0121 0.1660 1.0000
8.750 1.0527 0.01905 0.01126 -0.0096 0.1504 1.0000
9.000 1.0649 0.01977 0.01196 -0.0072 0.1395 1.0000
9.250 1.0758 0.02053 0.01266 -0.0047 0.1303 1.0000
9.500 1.0884 0.02116 0.01333 -0.0025 0.1217 1.0000
9.750 1.0994 0.02189 0.01407 -0.0001 0.1152 1.0000
10.000 1.1108 0.02259 0.01481 0.0022 0.1085 1.0000
10.250 1.1200 0.02341 0.01566 0.0046 0.1019 1.0000
10.500 1.1259 0.02426 0.01653 0.0075 0.0947 1.0000
10.750 1.1324 0.02521 0.01756 0.0100 0.0864 1.0000
11.000 1.1353 0.02653 0.01890 0.0125 0.0766 1.0000
11.250 1.1404 0.02792 0.02034 0.0144 0.0618 1.0000
11.500 1.1455 0.02947 0.02187 0.0159 0.0514 1.0000
11.750 1.1490 0.03128 0.02365 0.0172 0.0459 1.0000
12.000 1.1540 0.03307 0.02548 0.0182 0.0419 1.0000
12.250 1.1544 0.03538 0.02779 0.0191 0.0394 1.0000
12.500 1.1583 0.03747 0.03001 0.0199 0.0374 1.0000
12.750 1.1613 0.03968 0.03229 0.0205 0.0358 1.0000
13.000 1.1627 0.04209 0.03474 0.0210 0.0345 1.0000
13.250 1.1616 0.04474 0.03739 0.0218 0.0335 1.0000
13.500 1.1656 0.04696 0.03973 0.0225 0.0326 1.0000
13.750 1.1697 0.04920 0.04209 0.0230 0.0317 1.0000
14.000 1.1734 0.05152 0.04452 0.0235 0.0307 1.0000
14.250 1.1765 0.05392 0.04699 0.0238 0.0298 1.0000
14.500 1.1794 0.05633 0.04945 0.0240 0.0289 1.0000
14.750 1.1831 0.05867 0.05181 0.0246 0.0281 1.0000
15.000 1.1893 0.06089 0.05407 0.0259 0.0275 1.0000
15.250 1.1905 0.06373 0.05710 0.0259 0.0272 1.0000
15.500 1.1903 0.06681 0.06037 0.0258 0.0269 1.0000
15.750 1.1886 0.07018 0.06392 0.0256 0.0266 1.0000
16.000 1.1842 0.07395 0.06790 0.0250 0.0264 1.0000
16.250 1.1778 0.07812 0.07227 0.0240 0.0262 1.0000
16.500 1.1689 0.08279 0.07715 0.0227 0.0261 1.0000
16.750 1.1574 0.08800 0.08257 0.0208 0.0260 1.0000
17.000 1.1432 0.09385 0.08864 0.0184 0.0260 1.0000
17.250 1.1265 0.10040 0.09542 0.0153 0.0260 1.0000
17.500 1.1068 0.10774 0.10298 0.0115 0.0261 1.0000
17.750 1.0845 0.11599 0.11145 0.0069 0.0263 1.0000
18.000 1.0589 0.12536 0.12103 0.0014 0.0265 1.0000
18.250 1.0301 0.13602 0.13188 -0.0051 0.0269 1.0000
18.500 0.9976 0.14836 0.14439 -0.0127 0.0273 1.0000
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