RAF 34 AIRFOIL (raf34-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 34 AIRFOIL (raf34-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.84 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf34-il-1000000.txt Download as CSV file: xf-raf34-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 34 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9428 0.09648 0.09434 -0.0204 1.0000 0.0160
-16.500 -0.9900 0.08318 0.08086 -0.0286 1.0000 0.0158
-16.250 -1.0309 0.07111 0.06860 -0.0367 1.0000 0.0158
-16.000 -1.0766 0.05843 0.05567 -0.0462 1.0000 0.0157
-15.750 -1.0864 0.05279 0.04989 -0.0505 1.0000 0.0158
-15.500 -1.1014 0.04714 0.04406 -0.0543 1.0000 0.0158
-15.250 -1.1317 0.04058 0.03726 -0.0571 1.0000 0.0160
-15.000 -1.1417 0.03717 0.03371 -0.0575 1.0000 0.0162
-14.750 -1.1424 0.03501 0.03146 -0.0570 1.0000 0.0164
-14.500 -1.1351 0.03376 0.03017 -0.0562 1.0000 0.0166
-14.250 -1.1329 0.03217 0.02849 -0.0549 1.0000 0.0167
-14.000 -1.1224 0.03140 0.02769 -0.0536 1.0000 0.0170
-13.750 -1.1119 0.03070 0.02695 -0.0522 1.0000 0.0172
-13.500 -1.1042 0.02979 0.02597 -0.0503 1.0000 0.0174
-13.250 -1.0979 0.02883 0.02492 -0.0480 1.0000 0.0177
-13.000 -1.0875 0.02829 0.02432 -0.0459 1.0000 0.0180
-12.750 -1.0790 0.02763 0.02359 -0.0433 1.0000 0.0184
-12.500 -1.0731 0.02678 0.02263 -0.0403 1.0000 0.0186
-12.250 -1.0629 0.02618 0.02194 -0.0376 1.0000 0.0189
-12.000 -1.0495 0.02558 0.02125 -0.0356 1.0000 0.0192
-11.750 -1.0347 0.02509 0.02067 -0.0337 1.0000 0.0193
-11.500 -1.0310 0.02293 0.01833 -0.0306 1.0000 0.0199
-11.250 -1.0153 0.02229 0.01767 -0.0288 1.0000 0.0203
-11.000 -0.9981 0.02177 0.01712 -0.0272 1.0000 0.0206
-10.750 -0.9798 0.02141 0.01673 -0.0257 1.0000 0.0209
-10.500 -0.9621 0.02089 0.01617 -0.0241 1.0000 0.0213
-10.250 -0.9433 0.02055 0.01578 -0.0226 1.0000 0.0218
-10.000 -0.9248 0.02008 0.01525 -0.0210 1.0000 0.0223
-9.750 -0.9067 0.01949 0.01459 -0.0193 1.0000 0.0227
-9.500 -0.8847 0.01904 0.01407 -0.0184 0.9990 0.0231
-9.250 -0.8473 0.01863 0.01358 -0.0207 0.9763 0.0235
-9.000 -0.8001 0.01663 0.01145 -0.0259 0.9527 0.0244
-8.750 -0.7531 0.01592 0.01065 -0.0305 0.9157 0.0252
-8.500 -0.7292 0.01557 0.01014 -0.0298 0.8799 0.0257
-8.250 -0.7079 0.01521 0.00965 -0.0285 0.8570 0.0261
-8.000 -0.6860 0.01485 0.00918 -0.0273 0.8391 0.0266
-7.750 -0.6633 0.01453 0.00877 -0.0263 0.8236 0.0272
-7.500 -0.6404 0.01421 0.00835 -0.0253 0.8097 0.0278
-7.000 -0.5930 0.01363 0.00760 -0.0236 0.7846 0.0284
-6.750 -0.5702 0.01315 0.00704 -0.0226 0.7732 0.0287
-6.500 -0.5508 0.01232 0.00613 -0.0211 0.7625 0.0297
-6.250 -0.5278 0.01191 0.00567 -0.0201 0.7516 0.0303
-6.000 -0.5040 0.01159 0.00531 -0.0193 0.7418 0.0310
-5.500 -0.4555 0.01103 0.00464 -0.0178 0.7225 0.0322
-5.250 -0.4309 0.01079 0.00433 -0.0170 0.7138 0.0328
-5.000 -0.4058 0.01056 0.00406 -0.0164 0.7046 0.0335
-4.750 -0.3806 0.01036 0.00380 -0.0158 0.6965 0.0340
-4.500 -0.3549 0.01019 0.00359 -0.0153 0.6881 0.0345
-4.250 -0.3309 0.00986 0.00319 -0.0144 0.6805 0.0359
-4.000 -0.3055 0.00964 0.00294 -0.0138 0.6726 0.0372
-3.750 -0.2800 0.00947 0.00273 -0.0132 0.6654 0.0387
-3.500 -0.2539 0.00930 0.00255 -0.0128 0.6579 0.0401
-3.000 -0.2023 0.00896 0.00219 -0.0117 0.6441 0.0490
-2.750 -0.1789 0.00860 0.00201 -0.0108 0.6373 0.0947
-2.500 -0.1536 0.00839 0.00190 -0.0103 0.6308 0.1217
-2.250 -0.1281 0.00820 0.00179 -0.0098 0.6240 0.1462
-2.000 -0.1034 0.00799 0.00168 -0.0091 0.6177 0.1838
-1.750 -0.0796 0.00765 0.00159 -0.0084 0.6114 0.2513
-1.500 -0.0555 0.00740 0.00150 -0.0076 0.6050 0.3085
-1.250 -0.0325 0.00705 0.00141 -0.0067 0.5990 0.3825
-1.000 -0.0122 0.00656 0.00132 -0.0052 0.5927 0.5020
-0.750 0.0077 0.00620 0.00126 -0.0035 0.5864 0.6040
-0.500 0.0270 0.00583 0.00124 -0.0016 0.5804 0.6972
-0.250 0.0485 0.00565 0.00123 -0.0001 0.5739 0.7582
0.000 0.0726 0.00555 0.00123 0.0010 0.5676 0.7983
0.250 0.0976 0.00546 0.00124 0.0018 0.5598 0.8332
0.500 0.1244 0.00540 0.00128 0.0023 0.5514 0.8731
0.750 0.1554 0.00541 0.00133 0.0018 0.5417 0.9002
1.000 0.1907 0.00546 0.00139 0.0003 0.5330 0.9192
1.250 0.2280 0.00557 0.00148 -0.0016 0.5238 0.9332
1.500 0.2631 0.00568 0.00157 -0.0030 0.5153 0.9445
1.750 0.2996 0.00584 0.00169 -0.0047 0.5061 0.9522
2.000 0.3314 0.00596 0.00178 -0.0054 0.4972 0.9581
2.250 0.3687 0.00610 0.00187 -0.0074 0.4877 0.9599
2.500 0.4044 0.00626 0.00197 -0.0091 0.4757 0.9621
2.750 0.4389 0.00639 0.00208 -0.0104 0.4650 0.9653
3.000 0.4670 0.00655 0.00219 -0.0104 0.4556 0.9708
3.250 0.5051 0.00670 0.00230 -0.0126 0.4447 0.9721
3.500 0.5415 0.00682 0.00239 -0.0145 0.4340 0.9735
3.750 0.5764 0.00695 0.00248 -0.0160 0.4227 0.9752
4.000 0.6096 0.00709 0.00258 -0.0172 0.4098 0.9774
4.250 0.6402 0.00726 0.00270 -0.0179 0.3958 0.9805
4.500 0.6700 0.00743 0.00283 -0.0184 0.3824 0.9834
4.750 0.7054 0.00759 0.00292 -0.0202 0.3659 0.9845
5.000 0.7401 0.00776 0.00303 -0.0218 0.3474 0.9859
5.250 0.7740 0.00795 0.00316 -0.0233 0.3305 0.9876
5.500 0.8066 0.00817 0.00331 -0.0245 0.3105 0.9897
5.750 0.8377 0.00843 0.00348 -0.0255 0.2906 0.9920
6.000 0.8679 0.00871 0.00367 -0.0262 0.2663 0.9940
6.250 0.9006 0.00902 0.00385 -0.0277 0.2379 0.9953
6.500 0.9313 0.00949 0.00412 -0.0288 0.1994 0.9971
6.750 0.9601 0.01020 0.00454 -0.0297 0.1468 0.9990
7.000 0.9884 0.01061 0.00485 -0.0303 0.1278 1.0000
7.250 1.0074 0.01095 0.00514 -0.0288 0.1167 1.0000
7.500 1.0268 0.01125 0.00541 -0.0274 0.1078 1.0000
7.750 1.0462 0.01154 0.00568 -0.0260 0.0975 1.0000
8.000 1.0592 0.01226 0.00617 -0.0236 0.0609 1.0000
8.250 1.0729 0.01291 0.00672 -0.0213 0.0448 1.0000
8.500 1.0893 0.01336 0.00716 -0.0194 0.0393 1.0000
8.750 1.1055 0.01380 0.00759 -0.0174 0.0358 1.0000
9.000 1.1215 0.01424 0.00805 -0.0155 0.0330 1.0000
9.250 1.1383 0.01460 0.00844 -0.0136 0.0311 1.0000
9.500 1.1523 0.01510 0.00893 -0.0114 0.0288 1.0000
9.750 1.1663 0.01557 0.00944 -0.0091 0.0272 1.0000
10.000 1.1816 0.01594 0.00984 -0.0070 0.0258 1.0000
10.250 1.1945 0.01641 0.01032 -0.0047 0.0245 1.0000
10.500 1.2015 0.01713 0.01107 -0.0013 0.0228 1.0000
10.750 1.2119 0.01755 0.01152 0.0015 0.0222 1.0000
11.000 1.2169 0.01796 0.01199 0.0053 0.0213 1.0000
11.250 1.2221 0.01849 0.01255 0.0088 0.0207 1.0000
11.500 1.2283 0.01913 0.01322 0.0117 0.0200 1.0000
11.750 1.2317 0.02008 0.01420 0.0146 0.0191 1.0000
12.000 1.2362 0.02116 0.01534 0.0169 0.0183 1.0000
12.250 1.2460 0.02206 0.01630 0.0184 0.0179 1.0000
12.500 1.2553 0.02308 0.01738 0.0198 0.0172 1.0000
12.750 1.2644 0.02420 0.01854 0.0210 0.0166 1.0000
13.000 1.2717 0.02554 0.01992 0.0220 0.0160 1.0000
13.250 1.2769 0.02714 0.02157 0.0230 0.0156 1.0000
13.500 1.2746 0.02947 0.02398 0.0240 0.0151 1.0000
13.750 1.2797 0.03126 0.02584 0.0246 0.0148 1.0000
14.000 1.2858 0.03300 0.02766 0.0251 0.0145 1.0000
14.250 1.2916 0.03482 0.02955 0.0254 0.0141 1.0000
14.500 1.2954 0.03688 0.03168 0.0257 0.0140 1.0000
14.750 1.2977 0.03913 0.03400 0.0259 0.0136 1.0000
15.000 1.3021 0.04121 0.03613 0.0260 0.0133 1.0000
15.250 1.3022 0.04378 0.03877 0.0259 0.0130 1.0000
15.500 1.3021 0.04642 0.04148 0.0258 0.0128 1.0000
15.750 1.2987 0.04956 0.04468 0.0254 0.0124 1.0000
16.000 1.2935 0.05300 0.04820 0.0249 0.0123 1.0000
16.250 1.2828 0.05723 0.05253 0.0241 0.0121 1.0000
16.500 1.2792 0.06071 0.05609 0.0233 0.0118 1.0000
16.750 1.2778 0.06397 0.05945 0.0225 0.0117 1.0000
17.000 1.2764 0.06731 0.06287 0.0216 0.0115 1.0000
17.250 1.2696 0.07141 0.06707 0.0204 0.0116 1.0000
17.500 1.2687 0.07482 0.07056 0.0193 0.0112 1.0000
17.750 1.2601 0.07930 0.07514 0.0179 0.0111 1.0000
18.000 1.2556 0.08329 0.07921 0.0166 0.0110 1.0000
18.250 1.2505 0.08746 0.08345 0.0151 0.0108 1.0000
18.500 1.2462 0.09152 0.08759 0.0136 0.0107 1.0000
18.750 1.2373 0.09629 0.09245 0.0118 0.0107 1.0000
19.000 1.2297 0.10098 0.09723 0.0100 0.0106 1.0000
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